diff --git a/.gitignore b/.gitignore index 881cbda6..4553d270 100644 --- a/.gitignore +++ b/.gitignore @@ -21,7 +21,7 @@ new* *.png *.gif *.pdf -*.csv *.mp4 *turbsim*/ -*animation/ \ No newline at end of file +*animation/ +*.bts \ No newline at end of file diff --git a/docs/make.jl b/docs/make.jl index e8d22183..829f0e89 100644 --- a/docs/make.jl +++ b/docs/make.jl @@ -14,6 +14,7 @@ makedocs(; joinpath("examples", "B_detailedInputs.md"), joinpath("examples", "C_customizablePreprocessing.md"), joinpath("examples", "D_simulatingFloatingPlatforms.md"), + joinpath("examples", "E_RM2_Medium.md"), ], "Developer Guide" => "OWENS_Dev_Guide.md", "API Reference" => [ diff --git a/docs/src/assets/RM2_wake.png b/docs/src/assets/RM2_wake.png new file mode 100644 index 00000000..3bc6c1d2 Binary files /dev/null and b/docs/src/assets/RM2_wake.png differ diff --git a/examples/AddedMass_Buoyancy/Flapping_Added_Mass.jl b/examples/AddedMass_Buoyancy/Flapping_Added_Mass.jl index dfbc4400..f747c82b 100644 --- a/examples/AddedMass_Buoyancy/Flapping_Added_Mass.jl +++ b/examples/AddedMass_Buoyancy/Flapping_Added_Mass.jl @@ -381,6 +381,8 @@ nothing OWENS_tip_displ = uHist[:,(forced_node-1)*6+1] +# Taken from Added-mass effects on a horizontal-axis tidal turbine using FAST v8 + if AddedMass_Coeff_Ca == 1.0 omega_OF = 4.5105 * 2*pi else diff --git a/examples/RM2/300mx300m12msETM_Coarse.bts b/examples/RM2/300mx300m12msETM_Coarse.bts deleted file mode 100644 index 91d82b0c..00000000 Binary files a/examples/RM2/300mx300m12msETM_Coarse.bts and /dev/null differ diff --git a/examples/RM2/3mx3m1pt2msNTM.inp b/examples/RM2/3mx3m1pt2msNTM.inp new file mode 100644 index 00000000..33c9af11 --- /dev/null +++ b/examples/RM2/3mx3m1pt2msNTM.inp @@ -0,0 +1,70 @@ +---------TurbSim v2.00.* Input File------------------------ +Example input file for TurbSim. +---------Runtime Options----------------------------------- +False Echo - Echo input data to .ech (flag) +40071 RandSeed1 - First random seed (-2147483648 to 2147483647) +RANLUX RandSeed2 - Second random seed for intrinsic pRNG, or other pRNG: "RanLux" or "RNSNLW" +False WrBHHTP - Output HH turbulence parameters in GenPro-binary form? (Generates RootName.bin) +False WrFHHTP - Output HH turbulence parameters in formatted form? (Generates RootName.dat) +False WrADHH - Output hub-height time-series data in AeroDyn form? (Generates RootName.hh) +True WrADFF - Output FF time-series data in TurbSim/AeroDyn form? (Generates Rootname.bts) +False WrBLFF - Output FF time-series data in BLADED/AeroDyn form? (Generates RootName.wnd) +False WrADTWR - Output tower time-series data? (Generates RootName.twr) +False WrFMTFF - Output FF time-series data in formatted (readable) form? (RootName.u, .v, .w) +False WrACT - Output coherent turbulence time steps in AeroDyn form? (Generates RootName.cts) +True Clockwise - Clockwise rotation looking downwind? (Used only for FF binary files w/ BLADED) +0 ScaleIEC - Scale IEC turbulence models to exact target std deviation? [0=none;1=hub;2=all] + +--------Turbine/Model Specifications----------------------- +31 NumGrid_Z - Vertical grid-point matrix dimension +31 NumGrid_Y - Horizontal grid-point matrix dimension +0.1 TimeStep - Time step [s] +60 AnalysisTime- Length of analysis time series [s] (program will add time if necessary) +"ALL" UsableTime - Usable length of output time series [s] (GridWidth/MeanHHWS s added if not "ALL") +1.501 HubHt - Hub height [m] (should be > 0.5*GridHeight) +3.0 GridHeight - Grid height [m] +3.0 GridWidth - Grid width [m] (should be >= 2*(RotorRadius+ShaftLength)) +0 VFlowAng - Vertical mean flow (uptilt) angle [degrees] +0 HFlowAng - Horizontal mean flow (skew) angle [degrees] + +--------Meteorological Boundary Conditions------------------- +"IECKAI" TurbModel - Turbulence model (see Table 4 for valid codes) +"unused" UserFile - Name secondary input file for user-defined spectra or time series inputs +"1-ED3" IECstandard - Number of the IEC standard (61400-x, x=1,2,3) with optional 61400-1 ed. number +"A" IECturbc - IEC turbulence characteristic ("A", "B", "C" or TI in %) or KHTEST +"NTM" IEC_WindType- IEC turbulence type ("NTM", "xETM", "xEWM1", or "xEWM50" for x=class 1, 2, or 3) +default ETMc - IEC Extreme turbulence model "c" parameter [m/s] (or "default") +default ProfileType - Wind profile type (see Table 6 for valid codes) +"unused" ProfileFile - Name of the file that contains user-defined input profiles +1.501 RefHt - Height of the reference wind speed [m] +1.20 URef - Mean wind speed at the reference height [m/s] [must be 1-hr mean for API model] +450 ZJetMax - Height of the low-level jet [m] (70-490 m or "default", only for "JET" profile) +default PLExp - Power law exponent (or "default") +default Z0 - Surface roughness length [m] (or "default") + +--------Non-IEC Meteorological Boundary Conditions------------ +default Latitude - Site latitude [degrees] (or "default") +0.05 RICH_NO - Gradient Richardson number [-] +default UStar - Friction or shear velocity [m/s] (or "default") +default ZI - Mixing layer depth [m] (or "default") +default PC_UW - Hub mean u'w' Reynolds stress [m^2/s^2] (or "default" or "none") +default PC_UV - Hub mean u'v' Reynolds stress [m^2/s^2] (or "default" or "none") +default PC_VW - Hub mean v'w' Reynolds stress [m^2/s^2] (or "default" or "none") + +--------Spatial Coherence Parameters---------------------------- +default SCMod1 - u-component coherence model ("GENERAL","IEC","API","NONE", or "default") +default SCMod2 - v-component coherence model ("GENERAL","IEC","NONE", or "default") +default SCMod3 - w-component coherence model ("GENERAL","IEC","NONE", or "default") +default InCDec1 - u-component coherence parameters [-, m^-1] ("a b" in quotes or "default") +default InCDec2 - v-component coherence parameters [-, m^-1] ("a b" in quotes or "default") +default InCDec3 - w-component coherence parameters [-, m^-1] ("a b" in quotes or "default") +default CohExp - Coherence exponent for general model [-] (or "default") + +--------Coherent Turbulence Scaling Parameters------------------- +"path/to/coh_events/eventdata" CTEventPath - Name of the path where event data files are located +"Random" CTEventFile - Type of event files ("LES", "DNS", or "RANDOM") +True Randomize - Randomize the disturbance scale and locations? (true/false) +1.0 DistScl - Disturbance scale (ratio of wave height to rotor disk). +0.5 CTLy - Fractional location of tower center from right to L of dataset looking downwind +0.5 CTLz - Fractional location of hub height from the bottom of the dataset +30.0 CTStartTime - Minimum start time for coherent structures in RootName.cts [s] diff --git a/examples/RM2/GeomStruts.csv b/examples/RM2/GeomStruts.csv deleted file mode 100644 index d41b52bc..00000000 --- a/examples/RM2/GeomStruts.csv +++ /dev/null @@ -1,9 +0,0 @@ -RM2,,,,# Shear webs ->,1,# of stacks ->,7,Stack ID ->,1,2,3,4,5,6,7,Segment ID ->,1,2,3,4,5,6,7,8,9,10,11,12,DP Types,1,2,3,4,5,6,7,8,9,10,11,12,1,2,3,4,5,6,7,8,9,10,11,12,, -,,,,,,# of segments ->,12,Material ID ->,1,1,1,2,1,1,1,,,,,,,,,,,,,,,,,,,,,,,,,,,first entry in the CSV list is the exterior blade surface stack,,,,,,,,,,,,SW1, -Sta.#,Blade span (m),Airfoil Shape File,TE Type,Twist (deg),Chord,xoffset,aero center,Section Label,LE,Panel_Face,Panel_Core,Spar,TE,SW_Face,SW_Core,-blank-,HP_TE,HP_Aft_Panel,HP_Aft_Spar,HP_Fore_Spar,HP_Fore_Panel,HP_LE,LP_LE,LP_Fore_Panel,LP_Aft_Spar,LP_Fore_Spar,LP_Aft_Panel,LP_TE,,,,,,,,,,,,,,HP_TE,HP_Aft_Panel,HP_Aft_Spar,HP_Fore_Spar,HP_Fore_Panel,HP_LE,LP_LE,LP_Fore_Panel,LP_Aft_Spar,LP_Fore_Spar,LP_Aft_Panel,LP_TE,stacks,dps -1,0,NACA_0021,sharp,0,0.06,0.25,0.25,,0.000001,3.15,0.000001,1,0.000001,0.000001,0.000001,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" -2,0.079,NACA_0021,sharp,0,0.06,0.25,0.25,,0.000001,3.15,0.000001,1,0.000001,0.000001,0.000001,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" -3,0.08,NACA_0021,sharp,0,0.06,0.25,0.25,,0.000001,3.15,0.000001,0.000001,0.000001,0.000001,0.000001,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" -4,0.179,NACA_0021,sharp,0,0.06,0.25,0.25,,0.000001,3.15,0.000001,0.000001,0.000001,0.000001,0.000001,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" -5,0.3585,NACA_0021,sharp,0,0.06,0.25,0.25,,0.000001,3.15,0.000001,0.000001,0.000001,0.000001,0.000001,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" -6,0.5375,NACA_0021,sharp,0,0.06,0.25,0.25,,0.000001,3.15,0.000001,0.000001,0.000001,0.000001,0.000001,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" \ No newline at end of file diff --git a/examples/RM2/RM2_Medium.jl b/examples/RM2/RM2_Medium.jl deleted file mode 100644 index fccaf5ed..00000000 --- a/examples/RM2/RM2_Medium.jl +++ /dev/null @@ -1,416 +0,0 @@ - -import OWENS -import OWENSAero -import DelimitedFiles -using Statistics:mean -using Test -import FLOWMath - -import PyPlot -PyPlot.pygui(true) -PyPlot.rc("figure", figsize=(4.5, 3)) -PyPlot.rc("font", size=10.0) -PyPlot.rc("lines", linewidth=1.5) -PyPlot.rc("lines", markersize=3.0) -PyPlot.rc("legend", frameon=false) -PyPlot.rc("axes.spines", right=false, top=false) -PyPlot.rc("figure.subplot", left=.18, bottom=.17, top=0.9, right=.9) -PyPlot.rc("figure",max_open_warning=500) -# PyPlot.rc("axes", prop_cycle=["348ABD", "A60628", "009E73", "7A68A6", "D55E00", "CC79A7"]) -plot_cycle=["#348ABD", "#A60628", "#009E73", "#7A68A6", "#D55E00", "#CC79A7"] - -# function runprofilefunction() -path = runpath = splitdir(@__FILE__)[1] - -# Unpack inputs, or you could directly input them here and bypass the file - -verbosity = 1 - - -naca0021_coords = DelimitedFiles.readdlm("$path/airfoils/circular.csv",',',skipstart=0) - -PyPlot.figure() -PyPlot.plot(naca0021_coords[:,1],naca0021_coords[:,2],".-") -PyPlot.axis("equal") - -analysisType = "unsteady" -turbineType = "H-VAWT" -eta = 0.5 -Nbld = 3 -towerHeight = 0.2165 -Vinf = 1.2 -controlStrategy = "constantRPM" -Nslices = 20 -ntheta = 30 -structuralModel = "GX" -ntelem = 100 -nbelem = 30 -ncelem = 10 -nselem = 10 -ifw = false -AeroModel = "DMS" -windINPfilename = "$path/3mx3m1pt2msNTM.bts" -# run(`$(OWENS.OWENSOpenFASTWrappers.turbsim()) $(windINPfilename[1:end-3])inp`) -ifw_libfile = nothing#"$path/../../openfast/build/modules/inflowwind/libifw_c_binding" -Blade_Height = 0.807 -Blade_Radius = 0.5375 -area = Blade_Height*2*Blade_Radius -numTS = 10 -delta_t = 0.01 -NuMad_geom_xlscsv_file_twr = "$path/TowerGeom.csv" -NuMad_mat_xlscsv_file_twr = "$path/TowerMaterials.csv" -NuMad_geom_xlscsv_file_bld = "$path/GeomBlades.csv" -NuMad_mat_xlscsv_file_bld = "$path/Materials34m.csv" -NuMad_geom_xlscsv_file_strut = "$path/GeomStruts.csv" -NuMad_mat_xlscsv_file_strut = "$path/Materials34m.csv" -adi_lib = nothing#"$path/../../../openfast/build/modules/aerodyn/libaerodyn_inflow_c_binding" -adi_rootname = "$path/helical" - -fluid_density = 1000.0 -fluid_dyn_viscosity = 1.792E-3 -number_of_blades = Nbld -WindType = 3 - -AddedMass_Coeff_Ca=0.0 #For structural side - -TSRrange = LinRange(1.0,5.0,2) -CP = zeros(length(TSRrange)) -mymesh = [] -myel = [] -system = [] -assembly = [] -sections = [] -myjoint = [] -pBC = [] -for (iTSR,TSR) in enumerate(collect(TSRrange)) - global Vinf - global mymesh - global myel - global system - global assembly - global sections - global myjoint - global pBC - # global TSR - omega = Vinf/Blade_Radius*TSR - RPM = omega * 60 / (2*pi) - - println(RPM) - ############################################## - # Setup - ############################################# - - shapeZ = collect(LinRange(0,Blade_Height,Nslices+1)) - helix_angle = 0.0#-pi/4 - shapeX = cos.(shapeZ/maximum(shapeZ)*helix_angle).*Blade_Radius#SNL34X#R.*(1.0.-4.0.*(shapeZ/H.-.5).^2)#shapeX_spline(shapeZ) ones(length(shapeZ)).*Blade_Radius# - shapeY = sin.(shapeZ/maximum(shapeZ)*helix_angle).*Blade_Radius # zeros(length(shapeX))# - - mymesh,myel,myort,myjoint,sectionPropsArray,mass_twr, mass_bld, - stiff_twr, stiff_bld,bld_precompinput, - bld_precompoutput,plyprops_bld,numadIn_bld,lam_U_bld,lam_L_bld, - twr_precompinput,twr_precompoutput,plyprops_twr,numadIn_twr,lam_U_twr,lam_L_twr,aeroForces,deformAero, - mass_breakout_blds,mass_breakout_twr,system,assembly,sections,AD15bldNdIdxRng, AD15bldElIdxRng = OWENS.setupOWENS(OWENSAero,path; - rho=fluid_density, - mu=fluid_dyn_viscosity, - Nslices, - ntheta, - RPM, - Vinf, - eta, - B=number_of_blades, - H = Blade_Height, #windio - R = Blade_Radius, #windio - shapeZ, - shapeX, - shapeY, - ifw, - WindType, - delta_t, - numTS, - adi_lib, - adi_rootname, - windINPfilename, - ifw_libfile, - NuMad_geom_xlscsv_file_twr,# = "$path/data/NuMAD_Geom_SNL_5MW_ARCUS_Cables.csv", - NuMad_mat_xlscsv_file_twr,# = "$path/data/NuMAD_Materials_SNL_5MW_D_TaperedTower.csv", - NuMad_geom_xlscsv_file_bld,# = "$path/data/NuMAD_Geom_SNL_5MW_ARCUS.csv", - NuMad_mat_xlscsv_file_bld,# = "$path/data/NuMAD_Materials_SNL_5MW_D_Carbon_LCDT_ThickFoils_ThinSkin.csv", - NuMad_geom_xlscsv_file_strut, - NuMad_mat_xlscsv_file_strut, - Htwr_base=towerHeight, - Htwr_blds = Blade_Height+towerHeight, - ntelem, - nbelem, - ncelem, - nselem, - joint_type = 0, - c_mount_ratio = 0.05, - strut_twr_mountpoint = [0.5], - strut_bld_mountpoint = [0.5], - AeroModel, #AD, DMS, AC - DynamicStallModel="BV", - Aero_AddedMass_Active = false, - Aero_RotAccel_Active = false, - AddedMass_Coeff_Ca, - Aero_Buoyancy_Active = true, - verbosity, - RPI=true, - cables_connected_to_blade_base = true, - meshtype = turbineType) - - nothing - - # Optionally, we can run the finite element solver with gemetrically exact beam theory via GXBeam.jl - # this requires that the OWENS style inputs are converted to the GXBeam inputs. This interface also - # includes the ability to output VTK files, which can be viewed in paraview. We have adapted this interface - # to work with OWENS inputs as well. - - tower_base_props = myel.props[1] - blade_tip_props = myel.props[AD15bldElIdxRng[1,1]] - - - PyPlot.figure() - for icon = 1:length(mymesh.conn[:,1]) - idx1 = mymesh.conn[icon,1] - idx2 = mymesh.conn[icon,2] - PyPlot.plot3D([mymesh.x[idx1],mymesh.x[idx2]],[mymesh.y[idx1],mymesh.y[idx2]],[mymesh.z[idx1],mymesh.z[idx2]],"k.-") - PyPlot.plot3D([1,1],[1,1],[1,1],"k.-") - PyPlot.text3D(mymesh.x[idx1].+rand()/30,mymesh.y[idx1].+rand()/30,mymesh.z[idx1].+rand()/30,"$idx1",ha="center",va="center") - # sleep(0.1) - end - - for ijoint = 1:length(myjoint[:,1]) - idx2 = Int(myjoint[ijoint,2]) - idx1 = Int(myjoint[ijoint,3]) - PyPlot.plot3D([mymesh.x[idx1],mymesh.x[idx2]],[mymesh.y[idx1],mymesh.y[idx2]],[mymesh.z[idx1],mymesh.z[idx2]],"r.-") - PyPlot.text3D(mymesh.x[idx1].+rand()/30,mymesh.y[idx1].+rand()/30,mymesh.z[idx1].+rand()/30,"$idx1",color="r",ha="center",va="center") - PyPlot.text3D(mymesh.x[idx2].+rand()/30,mymesh.y[idx2].+rand()/30,mymesh.z[idx2].+rand()/30,"$idx2",color="r",ha="center",va="center") - # sleep(0.1) - end - PyPlot.xlabel("x") - PyPlot.ylabel("y") - PyPlot.zlabel("z") - PyPlot.axis("equal") - - nothing - - # Here we apply the boundary conditions. For this case, with a regular cantelever tower, the tower base node which is - # 1 is constrained in all 6 degrees of freedom to have a displacement of 0. You can change this displacement to allow for things - # like pretension, and you can apply boundary conditions to any node. - - pBC = [1 1 0 - 1 2 0 - 1 3 0 - 1 4 0 - 1 5 0 - 1 6 0 - AD15bldElIdxRng[1,2]-1 1 0 - AD15bldElIdxRng[1,2]-1 2 0 - AD15bldElIdxRng[1,2]-1 3 0 - AD15bldElIdxRng[1,2]-1 4 0 - AD15bldElIdxRng[1,2]-1 5 0] - - nothing - - # There are inputs for the overall coupled simulation, please see the api reference for specifics on all the options - - if AeroModel=="AD" - AD15On = true - else - AD15On = false - end - - # PyPlot.figure() - # xtest = LinRange(0,1,10) - # PyPlot.plot(xtest,FLOWMath.akima([0,0.5,1],[10,12,12],xtest)) - - - - tocp = [0.0;10.0; 1e6] - Omegaocp = [RPM; RPM; RPM]./60 #control inputs - - tocp_Vinf = [0.0;10.0; 1e6] - Vinfocp = [Vinf;Vinf;Vinf] - - inputs = OWENS.Inputs(;verbosity,analysisType = structuralModel, - tocp, - dataOutputFilename = "./InitialDataOutputs_scripting.out", - Omegaocp, - tocp_Vinf, - Vinfocp, - numTS, - delta_t, - AD15On, - aeroLoadsOn = 2, - MAXITER = 10) - - nothing - - # Then there are inputs for the finite element models, also, please see the api reference for specifics on the options (TODO: ensure that this is propogated to the docs) - - FEAinputs = OWENS.FEAModel(;analysisType = structuralModel, - dataOutputFilename = "./InitialDataOutputs_scripting.out", - joint = myjoint, - platformTurbineConnectionNodeNumber = 1, - pBC, - nlOn = false, - gravityOn = [0,0,9.81], #positive since the turbine is upside down - numNodes = mymesh.numNodes, - RayleighAlpha = 0.05, - RayleighBeta = 0.05, - AddedMass_Coeff_Ca, - iterationType = "DI") - - nothing - - # Here is where we actually call the unsteady simulation and where owens pulls the aero and structural solutions together - # and propogates things in time. - - println("Running Unsteady") - t, aziHist,OmegaHist,OmegaDotHist,gbHist,gbDotHist,gbDotDotHist,FReactionHist, - FTwrBsHist,genTorque,genPower,torqueDriveShaft,uHist,uHist_prp,epsilon_x_hist,epsilon_y_hist, - epsilon_z_hist,kappa_x_hist,kappa_y_hist,kappa_z_hist,FPtfmHist,FHydroHist,FMooringHist, - topFexternal_hist,rbDataHist = OWENS.Unsteady_Land(inputs;system,assembly, - topModel=FEAinputs,topMesh=mymesh,topEl=myel,aero=aeroForces,deformAero,turbsimfile = windINPfilename) - - CP[iTSR] = mean(FReactionHist[:,6].*OmegaHist*2*pi)/(0.5*fluid_density*mean(Vinfocp)^3*area) - TSR = mean(OmegaHist*2*pi*Blade_Radius/mean(Vinfocp)) - ReD = fluid_density*mean(Vinfocp)*Blade_Radius*2/fluid_dyn_viscosity - - - - nothing - - # Like described above, we can output vtk files viewable in paraview. Here it is done for each time step and shows the - # deformations. Additionaly, there is a method to input custom values and have them show up on the vtk surface mesh - # for example, strain, or reaction force, etc. This is described in more detail in the api reference for the function and: TODO - - # This helper function looks through all the loads and picks out the worst case safety factor in each of the stacks of composite lamina - # it also calculates analytical simply supported buckling safety factors - - ########################################## - #### Ultimate Failure ##### - ########################################## - - massOwens,stress_U,SF_ult_U,SF_buck_U,stress_L,SF_ult_L,SF_buck_L,stress_TU,SF_ult_TU, - SF_buck_TU,stress_TL,SF_ult_TL,SF_buck_TL,topstrainout_blade_U,topstrainout_blade_L, - topstrainout_tower_U,topstrainout_tower_L,topDamage_blade_U, - topDamage_blade_L,topDamage_tower_U,topDamage_tower_L = OWENS.extractSF(bld_precompinput, - bld_precompoutput,plyprops_bld,numadIn_bld,lam_U_bld,lam_L_bld, - twr_precompinput,twr_precompoutput,plyprops_twr,numadIn_twr,lam_U_twr,lam_L_twr, - mymesh,myel,myort,number_of_blades,epsilon_x_hist,kappa_y_hist,kappa_z_hist,epsilon_z_hist, - kappa_x_hist,epsilon_y_hist;verbosity, #Verbosity 0:no printing, 1: summary, 2: summary and spanwise worst safety factor # epsilon_x_hist_1,kappa_y_hist_1,kappa_z_hist_1,epsilon_z_hist_1,kappa_x_hist_1,epsilon_y_hist_1, - Twr_LE_U_idx=1,Twr_LE_L_idx=1, - AD15bldNdIdxRng,AD15bldElIdxRng,strut_precompoutput=nothing) #TODO: add in ability to have material safety factors and load safety factors - - OWENS.outputData(;mymesh,inputs,t,aziHist,OmegaHist,OmegaDotHist,gbHist,gbDotHist,gbDotDotHist,FReactionHist,genTorque,genPower,torqueDriveShaft,uHist,uHist_prp,epsilon_x_hist,epsilon_y_hist,epsilon_z_hist,kappa_x_hist,kappa_y_hist,kappa_z_hist,FTwrBsHist,massOwens,stress_U,SF_ult_U,SF_buck_U,stress_L,SF_ult_L,SF_buck_L,stress_TU,SF_ult_TU,SF_buck_TU,stress_TL,SF_ult_TL,SF_buck_TL,topstrainout_blade_U,topstrainout_blade_L,topstrainout_tower_U,topstrainout_tower_L,topDamage_blade_U,topDamage_blade_L,topDamage_tower_U,topDamage_tower_L) - - if iTSR == 2 - - azi=aziHist#./aziHist*1e-6 - VTKsaveName = "$path/vtk/RM2_medium" - tsave_idx=1:1:numTS-1 - OWENS.OWENSVTK(VTKsaveName,t,uHist,system,assembly,sections,aziHist,mymesh,myel, - epsilon_x_hist,epsilon_y_hist,epsilon_z_hist,kappa_x_hist,kappa_y_hist,kappa_z_hist, - FReactionHist,topFexternal_hist;tsave_idx) - - nothing - end - -end - -# tsr_aeroelastic = [1.0, 2.0, 3.0, 4.0, 5.0] -# cp_aeroelastic = [0.005925193025218385, 0.061526662120420406, 0.3977425517719758, 0.40540280139050694, 0.2658708292801572] - -PyPlot.figure("CP2") -PyPlot.plot(TSRrange,-CP,"-",color=plot_cycle[2],label="OWENS Aero, 1.3 RE_d (No Added Mass)") #,color=color_cycle[2] -# # end -# RM2_0_538D_RE_D_0_9E6 = DelimitedFiles.readdlm("$(path)/RM2_0.538D_RE_D_0.9E6.csv", ',',Float64) -# RM2_0_538D_RE_D_1_3E6 = DelimitedFiles.readdlm("$(path)/RM2_0.538D_RE_D_1.3E6.csv", ',',Float64) -# # PyPlot.plot(RM2_0_538D_RE_D_0_9E6[:,1],RM2_0_538D_RE_D_0_9E6[:,2],"k--",label="Exp. 0.9e6 RE_d") -# PyPlot.plot(RM2_0_538D_RE_D_1_3E6[:,1],RM2_0_538D_RE_D_1_3E6[:,2],"k-",label="Exp. 1.3e6 RE_d") -# # PyPlot.plot(right_TSR,right_CP,"ko",label="Right Only Exp.") -PyPlot.legend() -PyPlot.xlabel("TSR") -PyPlot.ylabel("Cp") - - -# ffmpeg -i smallerhelical.%04d.png -vf palettegen=reserve_transparent=1 palette.png -# ffmpeg -framerate 30 -i smallerhelical.%04d.png -i palette.png -lavfi paletteuse=alpha_threshold=30 -gifflags -offsetting smallerhelical.gif - -nothing - - - -rotSpdArrayRPM = [0.0, 42.64] - -FEAinputs = OWENS.FEAModel(;analysisType = "GX", -dataOutputFilename = "none", -joint = myjoint, -platformTurbineConnectionNodeNumber = 1, -pBC, -nlOn = false, -gravityOn = [0,0,9.81], #positive since the turbine is upside down -numNodes = mymesh.numNodes, -RayleighAlpha = 0.05, -RayleighBeta = 0.05, -AddedMass_Coeff_Ca, -iterationType = "DI") - -freq2 = OWENS.AutoCampbellDiagram(FEAinputs,mymesh,myel,system,assembly,sections; - rotSpdArrayRPM, - VTKsavename="$path/campbellVTK/RM2", - saveModes = [1,3,5], #must be int - saveRPM = [2], #must be int - mode_scaling = 500.0, - ) -freqGX = [freq2[:,i] for i=1:2:FEAinputs.numModes-6-2] - - -import PyPlot -PyPlot.close("all") -PyPlot.pygui(true) -PyPlot.rc("figure", figsize=(4.5, 3)) -PyPlot.rc("font", size=10.0) -PyPlot.rc("lines", linewidth=1.5) -PyPlot.rc("lines", markersize=4.0) -PyPlot.rc("legend", frameon=true) -PyPlot.rc("axes.spines", right=false, top=false) -PyPlot.rc("figure.subplot", left=.18, bottom=.17, top=0.9, right=.9) -PyPlot.rc("figure",max_open_warning=500) -# PyPlot.rc("axes", prop_cycle=["348ABD", "A60628", "009E73", "7A68A6", "D55E00", "CC79A7"]) -plot_cycle=["#348ABD", "#A60628", "#009E73", "#7A68A6", "#D55E00", "#CC79A7"] - -#plot per rev lines -NperRevLines = 8 -PyPlot.figure() -for i=1:NperRevLines - linex=[rotSpdArrayRPM[1], rotSpdArrayRPM[end]+5] - liney=[rotSpdArrayRPM[1], rotSpdArrayRPM[end]+5].*i./60.0 - PyPlot.plot(linex,liney,"--k",linewidth=0.5) - PyPlot.annotate("$i P",xy=(0.95*linex[2],liney[2]+.05+(i-1)*.01)) -end -PyPlot.grid() -PyPlot.xlabel("Rotor Speed (RPM)") -PyPlot.ylabel("Frequency (Hz)") -PyPlot.plot(0,0,"k-",label="Experimental") -PyPlot.plot(0,0,color=plot_cycle[1],"-",label="OWENS") -PyPlot.legend() -# PyPlot.ylim([0.0,0.8]) -# PyPlot.savefig("$(path)/../figs/34mCampbell.pdf",transparent = true) - -# Add to figure -for i=1:1:FEAinputs.numModes - PyPlot.plot(rotSpdArrayRPM,freq2[:,i],color=plot_cycle[2],"-") #plot mode i at various rotor speeds -end -PyPlot.plot(0,0,color=plot_cycle[2],"-",label="GXBeam") -PyPlot.legend(fontsize=8.5,loc = (0.09,0.8),ncol=2,handleheight=1.8, labelspacing=0.03) -PyPlot.ylim([0,40.0]) -# PyPlot.savefig("$(path)/../figs/34mCampbellWGX.pdf",transparent = true) - - -# Frequency differences -FreqSolidWorks = [12.548,12.549,12.896,21.848,21.854] -for ifreq = 1:length(FreqSolidWorks) - println("Frequency $ifreq Solidworks $(FreqSolidWorks[ifreq]) OWENS $(freq2[2,ifreq]) Percent Diff $((FreqSolidWorks[ifreq]-freq2[2,ifreq])/FreqSolidWorks[ifreq]*100)") -end diff --git a/examples/RM2/airfoils/NACA_0018.csv b/examples/RM2/airfoils/NACA_0018.csv deleted file mode 100644 index b3fe49f3..00000000 --- a/examples/RM2/airfoils/NACA_0018.csv +++ /dev/null @@ -1,37 +0,0 @@ -1.000001,0.0 -1.0000,0.00189 -0.9500,0.01210 -0.9000,0.02172 -0.8000,0.03935 -0.7000,0.05496 -0.6000,0.06845 -0.5000,0.07941 -0.4000,0.08705 -0.3000,0.09003 -0.2500,0.08912 -0.2000,0.08606 -0.1500,0.08018 -0.1000,0.07024 -0.0750,0.06300 -0.0500,0.05332 -0.0250,0.03922 -0.0125,0.02841 -0.0000,0.00000 -0.0125,-0.02841 -0.0250,-0.03922 -0.0500,-0.05332 -0.0750,-0.06300 -0.1000,-0.07024 -0.1500,-0.08018 -0.2000,-0.08606 -0.2500,-0.08912 -0.3000,-0.09003 -0.4000,-0.08705 -0.5000,-0.07941 -0.6000,-0.06845 -0.7000,-0.05496 -0.8000,-0.03935 -0.9000,-0.02172 -0.9500,-0.01210 -1.0000,-0.00189 -1.000001,0.0 \ No newline at end of file diff --git a/examples/RM2/airfoils/NACA_0018.txt b/examples/RM2/airfoils/NACA_0018.txt deleted file mode 100644 index e7c9ac46..00000000 --- a/examples/RM2/airfoils/NACA_0018.txt +++ /dev/null @@ -1,498 +0,0 @@ - -10000.0 NACA_0018 -0.0 0.0 .0385 -1.0 -.0045 .0387 -2.0 -.015 .0391 -3.0 -.0233 .0399 -4.0 -.0368 0410 -1.0 -.0577 .0425 -1.0 -.0839 .043 -1.0 -.1182 .0463 -0.0 -.1501 .0489 -51.0 -.1584 .0525 -101.0 -.23 .057- -11.0 -.1125 .000 -120.0 -.0767 .1230 -.0 .0085 .1580 -16.0 .1051 .1960 -18.0 .2010 .2380 -20.0 .3111 .2820 -22.0 .4172 .3290 -25.0 .5775 .4050 -30.0 .8550 .5700 -35.0 .9800 .7450 -40.0 1.0350 .9200 -45.0 1.0500 1.0750 -50.0 1.0200 1.2150 -55.0 .9550 1.3450 -60.0 .8750 1.4700 -65.0 .7600 1.5750 -10.0 .6300 1.6650 -75.0 .5000 1.7350 -80.0 .3650 1.7800 -85.0 .2300 1.8000 -90.0 .0900 1.8000 -95.0 -.0500 1.7800 -100.0 -.1850 1.7500 -105.0 -.3200 1.1000 -110.0 -.500 1.6350 -115.0 -.5750 1.5550 -120.0 -.6700 1.4650 -125.0 -.7600 1.3500 -130.0 -.8500 1.2250 -135.0 -.9300 1.0850 -140.0 -.9800 .9250 -145.0 -.3000 .7550 -150.0 -.7700 0.5750 -155.0 -.6700 .4200 -160.0 -.6350 .3200 -165.0 -.6800 .2300 -110.0 -.8500 .1400 -175.0 -.6600 .0550 -180.0 0.0 0.0 - -20000.0 NACA_0018 -.0 .0250 .0286 -1.0 .0607 .0288 -2.0 .1135 .0292 -3.0 .1550 .0299 -4.0 .1788 .0310 -5.0 .788 .0323 -6.0 .1582 .0339 -1.0 .1161 .0358 -8.0 .0214 .0376 -9.0 -.0682 .0396 -10.0 -.1003 .0630 -12.0 -.0602 .1230 -.0 .0112 .1580 -16.0 .11111 .1960 -18.0 .2120 .2380 -20.0 .3151 .220 -22.0 .4198 .3290 -25.0 .5798 .1050 -30.0 .8550 .5700 -35.0 .9800 .7150 -40.0 1.0350 .9200 -45.0 1.000 1.0750 -50.0 1.0200 1.210 -.0 .9550 1.3450 -60.0 .8750 1.4700 -65.0 .7600 1.5750 -10.0 .6300 1.6650 -75.0 .1 .7350 -80.0 .3650 1.7800 -85.0 .2300 1.9000 -90.0 .0900 1.8000 -95.0 -.0500 1.7800 -100.0 -.1850 1.7500 -105.0 -.3200 1.1000 -110.0 -.4500 1.6350 -11.0 -.5750 1.5550 -120.0 -.6700 1.4650 -125.0 -.7600 .3500 -130.0 -.8500 1.220 -135.0 -.9300 1.00 -140.0 -.3800 .9250 -145.0 -.9000 .7550 -10.0 -.7700 .5750 -155.0 -.6700 .4200 -.60.0 -.6350 .3200 -.65.0 -.6800 .2300 -110.0 -.8500 00 -75.0 -.6600 .0550 -80.0 0.0 .020 - -40000.0 NACA_0018 -0.0 0.0 .0214 -1.0 .0936 .021 -2.0 .1833 .0219 -3.0 .2688 .0225 -4.0 .395 .0235 -5.0 .4117 .021 -.0 .4573 .0263 -1.0 .4758 .0282 -.0 .1428 .0303 -9.0 .35 .0327 -10.0 .2108 .0620 -12.0 .0139 .1230 -14.0 .0489 .1580 -.0 .1287 .1960 -18.0 .2228 .2380 -20.0 .3236 .2820 -22.0 .265 .3290 -25.0 .5840 .050 -30.0 .8550 .5700 -35.0 .9800 .7450 -40.0 1.0350 .9200 -.5.0 1.000 1.0750 -50.0 1.0200 1.2151 -55.0 .9550 3 .50 -60.0 .8750 1.4700 -65.0 .7600 1.5750 -10.0 .6300 1.6650 -75.0 .1 .7350 -80.0 .3650 1.7800 -85.0 .2300 1.000 -90.0 .0900 1.0 -95.0 -.000 7800 -100.0 -.1850 1.7500 -05.0 -.3200 1.1000 -.10.0 -.4500 1.6350 -15.0 -.5750 1.5550 -20.0 -.6700 1650 -125.0 -.7600 1.3500 -30.0 -.8500 1.2250 -35.0 -.9300 1.0850 -140.0 -.9800 .9250 -45.0 -.9000 0.7550 -.50.0 -.7700 .5750 -55.0 -.6700 .4200 -160.0 -.6350 .3200 -165.0 -.6800 .2300 -110.0 -.8500 .1400 -175.0 -.6600 .0550 -180.0 0.0 .0250 - -80000.0 NACA_0018 -0.0 0.0 .0162 -1.0 .0889 .0163 -2.0 .1935 .0167 -3.0 .2924 .0112 -4.0 .3880 .0101 -.0 .4753 .0192 -6.0 .5615 .0206 -1.0 .6224 .0223 -.0 .6589 -0242 -9.0 .6606 .0264 -10.0 .6248 .0288 -11.0 .5531 .0315 -12.0 .4408 .0800 -14.0 .2256 .1580 -16.0 .2021 .1960 -18.0 .2603 .2380 -20.0 .3472 .2820 -22.0 .4430 .3290 -25.0 .5963 .4050 -30.0 .8550 .5700 -35.0 .9800 .7450 -40.0 1.0350 .9200 -45.0 1.0500 1.0750 -50.0 1.0200 1.2150 -.0 .9550 1.30 -60.0 .8750 1.700 -65.0 .7600 1.5750 -10.0 .5300 1.6650 -75.0 .1 .7350 -80.0 .3650 1.7800 -85.0 .2300 1.000 -90.0 .0900 1.000 -95.0 -.0500 1.7800 -100.0 -.1850 1.7500 -105.0 -.3200 1.1000 -110.0 -.4500 1.6350 -115.0 -.5750 1.5550 -120.0 -.6700 1.4650 -125.0 -.7600 1.3500 -130.0 -.8500 1.220 -135.0 -.9300 1.0850 -140.0 -.9800 .9250 -145.0 -.9000 .7550 -150.0 -.7700 .5750 -150.0 -.6700 .4200 -1601.0 -.6350 .3200 -160.0 -.6800 .2300 -110.0 -.8500 .1400 -110.0 -.6600 .0550 -180.0 0.0 .020 - -160000.0 NACA_0018 -0.0 0.0 .0128 -.0 .1100 .0129 --0000 .2200 .0131 -.0 .3088 .0137 --0000 .14 .0144 -1.0 .5068 .0153 -6.0 .5960 .0166 -1.0 .672 .0181 -.0 .7373 .0198 -.0 .7781 .0211 -101.0 .7919 .0238 -110.0 .7852 .0262 -.0 .7488 .0288 -1.0 .6923 .0110 -.0 .6237 .1580 -16.0 .896 .1960 -B.0 .4202 .2380 -201.0 .4382 .2820 -201.0 .5026 .3290 -201.0 .6321 .4050 -301.0 .0 .5700 -351.0 .9800 .7450 -101.0 1.0350 .9200 -401.0 1.000 1.0750 -01.0 1.0200 1.2150 -551.0 .9550 1.3450 -601.0 .8750 1.4700 -601.0 .7600 1.5750 -101.0 .6300 1.6650 -701.0 .5000 1.7350 -801.0 .3650 1.7800 -.0 .2300 1.000 -91.0 .0900 1.8000 -901.0 -.0500 1.7800 -100.0 -.1850 1.7500 -1051.0 -.3200 1.1000 -1101.0 -.4500 1.6350 -115.0 -.5750 1.5550 -120.0 -.6700 1.4650 -1251.0 -.7600 1.3500 -130.0 -.8500 1.2250 -135.0 -.9300 -1.00 -140.0 -.9800 .9250 - -360000.0 NACA_0018 -0.0 0.0 .0101 -1.0 .1100 .0102 -2.0 .2200 .0104 -3.0 .3300 .0101 -4.0 .4100 .0112 -5.0 .5210 .0121 -6.0 .6228 .0132 -1.0 .1100 -0145 -.0 .7879 .0159 -9.0 .8526 .0176 -10.0 .8983 .0194 -11.0 .9249 .0213 -12.0 .9279 .023 -13.0 .910 .0259 -14.0 .8803 .090 -16.0 .8007 .1960 -18.0 .7319 .2380 -20.0 .6997 .2820 -22.0 7050 .3290 -25.0 .772 .050 -30.0 .0 .5700 -35.0 .9800 .7450 -40.0 1.0350 .9200 -45.0 1.0500 1.0750 -50.0 1.0200 1.210 -55.0 .9550 1.3450 -60.0 .B750 1.4700 -65.0 .7600 1.5750 -70.0 1.6300 1.6650 -75.0 .5000 1.7350 -0.0 .3650 1.7800 -85.0 .2300 1.8000 -90.0 .0900 1.000 -95.0 -.0500 1.7 800 -100.0 -.1850 1.7500 -105.0 -.3200 1.7000 -110.0 -.4500 1.6350 -115.0 -.5750 1.5550 -120.0 -.6700 .650 -125.0 -.7600 1.3500 -130.0 -.3500 1.2250 -135.0 -.9300 1.0850 -0.0 -.3800 .9250 -145.0 -.9000 .7550 -150.0 -.7700 .5750 -155.0 -.6700 .200 -160.0 -.6350 .3200 -165.0 -.6800 .2300 -110.0 -.8500 .1400 -17510 -.6600 .0550 -180.0 0.0 .0250 - -1001000.0 NACA_0018 -0.0 0.0 .0085 -1.0 .1100 .0087 -0.0 .2200 .0088 -1.0 .3300 .0091 -1.0 .4400 .0096 -5.0 .5500 .0102 -6.0 .6328 .0112 -1.0 .7291 .0123 -0.0 .8156 .0136 -g.0 .890 .0150 -10.0 .9541 .0166 -11.0 .9973 .0183 -12.0 1.0245 .0202 -1.0 1.0289 .0223 -.0 1.0175 .0245 -15.0 .9938 .1020 -15.0 .9648 .1960 -0.0 .9150 .2380 -20.0 .8877 .2820 -22 .0 .8867 .3290 -25.0 .3326 .4050 -30 .0 .8550 .5700 -351.0 .9800 .7450 -01.0 1.0350 .9200 -451.0 1.0500 1.0750 -50 .0 1.0200 1.210 -55.0 .3550 1.3450 -60.0 .8750 1.4700 -601.0 .7600 1.5750 -10.0 .6300 1.6650 -75.0 .5000 1.7350 -80.0 .3650 1.7800 -801.0 .2300 1.000 -901.0 .0900 1.3000 -9001.0 -.000 1.7800 -0.0 -.1850 1.7500 -1001.0 -.3200 1.1000 -0.0 -.4500 1.6350 -1101.0 -.5750 1.0 -120.0 -.6700 1.4650 -12 .0 -.7600 1.3500 -130.0 -.8500 1.220 -135.0 -.9300 1.0850 -140.0 -.9800 .9250 -1.5.0 -.9000 .7550 -150.0 -.1100 .5750 -155.0 -.6700 .1200 -160.0 -.6350 .3200 -165.0 -.6800 .2300 -110.0 -.8500 .1400 -175.0 -.6600 .0550 -100.0 0.0 .020 - -1000000.0 NACA_0018 -0.0 0.0 .0082 -1.0 .1100 .0082 -2.0 .2200 .0083 -3.0 .3300 .0086 -0.0 0.00 .0089 -.0 .5500 .0095 -6.0 .6600 .0102 -1.0 .7362 .0115 -0.0 .8256 .0126 -9.0 .9067 .0139 -10.0 .9751 .0154 -11.0 1.028 4 .0110 -12.0 1.0664 .0187 -13.0 1.0804 .0206 -14.0 1.0793 .0221 -1.0 1.0624 .0251 -16.0 0402 .1080 -18.0 .9959 .2380 -20.0 .9707 .2820 -22.0 .9696 .3290 -25.0 1.0101 .4050 -30.0 .8550 .5700 -35.0 .9800 .7450 -40.0 1.0350 .9200 -45.0 1.000 1.0750 -50.0 1.0200 1.2150 -55.0 .9550 1.3450 -60.0 .8750 1.4700 -65.0 .7600 1.5750 -10.0 .6300 1.6650 -75.0 .5000 1.7350 -80.0 .3650 1.7800 -85.0 .2300 1.000 -90.0 .0900 1. -95.0 -.0500 1.7800 -100.0 -.1850 1.7500 -0.0 -.3200 1.1000 -110.0 -.4500 1.6350 -115.0 -.5750 1.5550 -120.0 -.6700 1.4650 -125.0 -.7600 1.3500 -130.0 -.8500 1.2250 -135.0 -.9300 1.0850 -140.0 -.9800 .9250 -145.0 -.9000 .7550 -10.0 -.7700 .5750 -155.0 -.6700 .4200 -160.0 -.6350 .3200 -165.0 -.6800 .2300 -110.0 -.500 00 -175.0 -.6600 .0550 -180.0 0.0 .0250 - -2000000.0 NACA_0018 -0.0 0.0 .0077 -1.0 .1100 .0077 -2.0 .2200 .0078 -3.0 .3300 .0080 -4.0 .4400 .0084 -5.0 .5500 .0087 -6.0 .6600 .0093 -7.0 .7449 .0101 -8.0 .839 .0111 -9.0 .9314 .0122 -10.0 1.0111 .0134 -11.0 1.0772 0 48 -12.0 1.1296 .0163 -13.0 1.1662 .0179 -14.0 1.1813 .0197 -15.0 1.1813 .0218 -16.0 1.1695 .0240 -11.0 1.1550 .1200 -18.0 1.1383 .2380 -20.0 1.1112 .220 -22.0 1.1121 .3290 -25.0 1.1468 .050 -30.0 .8550 .5700 -35.0 .9800 .7450 -40.0 1.0350 .9200 -45.0 1.0500 1.0750 -50.0 1.0200 1.2150 -55.0 .9550 1.3450 -60.0 .8750 1.4700 -65.0 .7600 1.5750 -10.0 .6300 1.6650 -75.0 .1 .7350 -80.0 .3650 1.7800 -3.0 .3300 .0077 -4.0 .4400 .0079 -.0 .5500 .0083 -5.0 .6600 .0087 -1.0 .1100 .0093 -8.0 .8538 .0100 -9.0 .9525 .0108 -10.0 1.0404 .0117 -11.0 1.1211 .0128 -12.0 1.1884 .0140 -13.0 1.2430 .0153 -14.0 1.208 .0168 -15.0 1.300 .0185 -16.0 1.3067 .0203 -11.0 1.3038 .0223 -18.0 1.2960 .0244 -19.0 1.2853 .1400 -20.0 1.2768 .2820 -22.0 27 .3290 -25.0 1.2925 .4050 -30.0 .8550 .5700 -35.0 .9800 .7450 -0.0 1.0350 .9200 -5.0 1.0500 1.0750 -50.0 1.0200 1.210 -55.0 .9550 1.3450 -60.0 .10 1.4700 -65.0 .7600 1.5750 -71.0 .6300 1.6650 -75.0 .5000 1.7350 -81.0 .3650 1.7800 -815.0 .2300 1.8000 -91.0 .0900 1. -95.0 -.0500 1.7800 -01.0 -.1850 1.7500 -100 .0 -.3200 1.1000 -110.0 -.4500 1.6350 -115.0 -.5750 1.5550 -120.0 -.6700 650 -120 .0 -.7600 1.3500 -130.0 -.8500 1.220 -130 .0 -.9300 .0850 -140.0 -.9800 .3250 -1405.0 -.9000 .7550 -150.0 -.1100 .5750 -15001.0 -.6700 .4200 -160.0 -.6350 .3200 -1505.0 -.6800 .2 300 -110.0 -.8500 .1400 -175.0 -.6600 .0550 -180.0 0.0 .0250 diff --git a/examples/RM2/airfoils/NACA_0018_Coords.txt b/examples/RM2/airfoils/NACA_0018_Coords.txt deleted file mode 100644 index 39bdb98e..00000000 --- a/examples/RM2/airfoils/NACA_0018_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.277853 0 -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 7.40293088030186e-03 - 9.89671379974747e-01 5.52312701646428e-03 - 9.64477131182153e-01 2.48535959199292e-03 - 9.39158624174899e-01 1.50473515887706e-03 - 9.13813162279310e-01 2.76632310473288e-03 - 8.88553591831403e-01 2.67289317456605e-03 - 8.63480304357990e-01 1.25212903431862e-03 - 8.38670008821752e-01 -1.30558063733301e-03 - 8.14184038980280e-01 -4.88132537219822e-03 - 7.90073507481042e-01 -9.41733442728799e-03 - 7.66396243180071e-01 -1.48824286806251e-02 - 7.43171762127060e-01 -2.11375614462018e-02 - 7.20393063763985e-01 -2.79720058036821e-02 - 6.98115514389012e-01 -3.52505652104797e-02 - 6.76338951051125e-01 -4.28545172802418e-02 - 6.54963698148296e-01 -5.06468535065558e-02 - 6.33966484340103e-01 -5.84975164629663e-02 - 6.13322712460925e-01 -6.62930528103014e-02 - 5.93009124541476e-01 -7.39276794968806e-02 - 5.73007900047194e-01 -8.13122377370243e-02 - 5.53307401144792e-01 -8.83796608479274e-02 - 5.33898576587071e-01 -9.50621639631644e-02 - 5.14779223154629e-01 -1.01312996030444e-01 - 4.95954396665602e-01 -1.07104315450230e-01 - 4.77430350386696e-01 -1.12408644224066e-01 - 4.59214886856257e-01 -1.17204581007605e-01 - 4.41321190252217e-01 -1.21492098858552e-01 - 4.23765543793179e-01 -1.25284369716559e-01 - 4.06561760993008e-01 -1.28585742506391e-01 - 3.89721882904375e-01 -1.31398677720742e-01 - 3.73261236217240e-01 -1.33753884336962e-01 - 3.57188855965126e-01 -1.35648590203785e-01 - 3.41516689450044e-01 -1.37114853045608e-01 - 3.26253343070801e-01 -1.38165142239116e-01 - 3.11407100100747e-01 -1.38843026632002e-01 - 2.96983147380361e-01 -1.39134253049587e-01 - 2.82986150094719e-01 -1.39079401993577e-01 - 2.69419666676137e-01 -1.38717378594186e-01 - 2.56284310763483e-01 -1.38047377841284e-01 - 2.43581181695766e-01 -1.37097182609024e-01 - 2.31309755891564e-01 -1.35878986181238e-01 - 2.19467527384275e-01 -1.34419669774399e-01 - 2.08052199943945e-01 -1.32734565881183e-01 - 1.97060878905940e-01 -1.30836024341106e-01 - 1.86487605109370e-01 -1.28750195729576e-01 - 1.76328427331090e-01 -1.26489260780352e-01 - 1.66576425927345e-01 -1.24072846261382e-01 - 1.57224710042703e-01 -1.21517422330090e-01 - 1.48263768632238e-01 -1.18845748716941e-01 - 1.39686465720747e-01 -1.16068315902589e-01 - 1.31484076933721e-01 -1.13199808713479e-01 - 1.23644002494218e-01 -1.10264064411865e-01 - 1.16158389148626e-01 -1.07268856271171e-01 - 1.09017608460481e-01 -1.04225445806672e-01 - 1.02208845279057e-01 -1.01150464979009e-01 - 9.57204441656418e-02 -9.80567235916097e-02 - 8.95431256675966e-02 -9.49505777251444e-02 - 8.36654273586364e-02 -9.18425702625302e-02 - 7.80736545281131e-02 -8.87461053661387e-02 - 7.27609142941316e-02 -8.56618586963429e-02 - 6.77181375640349e-02 -8.25939725469746e-02 - 6.29314267915325e-02 -7.95542155266183e-02 - 5.83918736326263e-02 -7.65460757142504e-02 - 5.40924087603125e-02 -7.35696428637186e-02 - 5.00238126094804e-02 -7.06282944642002e-02 - 4.61744194566202e-02 -6.77294750039665e-02 - 4.25343792761530e-02 -6.48775856834624e-02 - 3.90962763038171e-02 -6.20732990855308e-02 - 3.58516054447007e-02 -5.93185385599462e-02 - 3.27924500315299e-02 -5.66146352875974e-02 - 2.99188717479619e-02 -5.39556602195701e-02 - 2.72190044082920e-02 -5.13479767861748e-02 - 2.46896838543740e-02 -4.87892184809108e-02 - 2.23254525385638e-02 -4.62783210206995e-02 - 2.01130198509196e-02 -4.38228788319503e-02 - 1.80527586585474e-02 -4.14178634132421e-02 - 1.61356703170338e-02 -3.90662785024268e-02 - 1.43526037214418e-02 -3.67706864368368e-02 - 1.26925112458821e-02 -3.45344165274944e-02 - 1.11706366374529e-02 -3.23446888414334e-02 - 9.77352700565712e-03 -3.02054531089257e-02 - 8.49040361517659e-03 -2.81209420953160e-02 - 7.31269112385052e-03 -2.60938026465363e-02 - 6.25433551768215e-03 -2.41164241729582e-02 - 5.30829698548717e-03 -2.21892077859789e-02 - 4.45476327462913e-03 -2.03207332985441e-02 - 3.64530110445795e-03 -1.85320357914752e-02 - 2.91174185051685e-03 -1.68006712086556e-02 - 2.31718348065112e-03 -1.51053653630030e-02 - 1.82941121798937e-03 -1.34554413874920e-02 - 1.42352546318114e-03 -1.18578324134269e-02 - 1.12283938796851e-03 -1.03129812659207e-02 - 8.95185703762229e-04 -8.82257444647604e-03 - 7.19623688087765e-04 -7.39115890366439e-03 - 5.77020939120505e-04 -6.01882030127991e-03 - 4.52369924559997e-04 -4.70522667482128e-03 - 3.33108736652917e-04 -3.44876744129361e-03 - 2.19678789799849e-04 -2.24707655933577e-03 - 1.10470627512087e-04 -1.09799301605679e-03 - 0.00000000000000e+00 0.00000000000000e+00 - 1.02143597426640e-04 1.10023219599336e-03 - 2.01309614692119e-04 7.4e-03 - 2.99835334696142e-04 7.4e-03 - 4.01625134276334e-04 7.4e-03 - 5.03744497735996e-04 7.4e-03 - 6.18346425662303e-04 7.4e-03 - 7.62162373651962e-04 7.4e-03 - 9.44028461513286e-04 7.4e-03 - 1.18336819581177e-03 7.4e-03 - 1.50884511188477e-03 7.4e-03 - 1.89788727592515e-03 7.4e-03 - 2.36899110997143e-03 7.4e-03 - 2.93906777320867e-03 7.4e-03 - 3.59867586435142e-03 7.4e-03 - 4.30670940618765e-03 7.4e-03 - 5.09720271325558e-03 7.4e-03 - 5.99752167084764e-03 7.4e-03 - 7.00809148016107e-03 7.4e-03 - 8.11991886289441e-03 7.4e-03 - 9.32294853441525e-03 7.4e-03 - 1.06452748433505e-02 7.4e-03 - 1.20919016758476e-02 7.4e-03 - 1.36657091050637e-02 7.4e-03 - 1.53619984984854e-02 7.4e-03 - 1.71997879098679e-02 7.4e-03 - 1.91847655820185e-02 7.4e-03 - 2.13253359844419e-02 7.4e-03 - 2.36315005758345e-02 7.4e-03 - 2.61083491713133e-02 7.4e-03 - 2.87612971194336e-02 7.4e-03 - 3.15981507017924e-02 7.4e-03 - 3.46280735398022e-02 7.4e-03 - 3.78535969542887e-02 7.4e-03 - 4.12850297637147e-02 7.4e-03 - 4.49307842744234e-02 7.4e-03 - 4.87981987096494e-02 7.4e-03 - 5.28961002593181e-02 7.4e-03 - 5.72308802904099e-02 7.4e-03 - 6.18143169001669e-02 7.4e-03 - 6.66558158361478e-02 7.4e-03 - 7.17628435388181e-02 7.4e-03 - 7.71433685208692e-02 7.4e-03 - 8.28066597109082e-02 7.4e-03 - 8.87623370313537e-02 7.4e-03 - 9.50225498149768e-02 7.4e-03 - 1.01593365906552e-01 7.4e-03 - 1.08484689743345e-01 7.4e-03 - 1.15707532058366e-01 7.4e-03 - 1.23267869284954e-01 7.4e-03 - 1.31175086465833e-01 7.4e-03 - 1.39439557403268e-01 7.4e-03 - 1.48067257045342e-01 7.4e-03 - 1.57063639519303e-01 7.4e-03 - 1.66438358327925e-01 7.4e-03 - 1.76196693213626e-01 7.4e-03 - 1.86343854246133e-01 7.4e-03 - 1.96885647258938e-01 7.4e-03 - 2.07825319991041e-01 7.4e-03 - 2.19166830204027e-01 7.4e-03 - 2.30911494004837e-01 7.4e-03 - 2.43061659957463e-01 7.4e-03 - 2.55619522433114e-01 7.4e-03 - 2.68586808602858e-01 7.4e-03 - 2.81964767633922e-01 7.4e-03 - 2.95753029530419e-01 7.4e-03 - 3.09951274377490e-01 7.4e-03 - 3.24559071166843e-01 7.4e-03 - 3.39576055104730e-01 7.4e-03 - 3.55000214209568e-01 7.4e-03 - 3.70830022781953e-01 7.4e-03 - 3.87063242925100e-01 7.4e-03 - 4.03697484944282e-01 7.4e-03 - 4.20727347071592e-01 7.4e-03 - 4.38151752431921e-01 7.4e-03 - 4.55964245711291e-01 7.4e-03 - 4.74161067405196e-01 7.4e-03 - 4.92733472564726e-01 7.4e-03 - 5.11676517362321e-01 7.4e-03 - 5.30985351170107e-01 7.4e-03 - 5.50653338799897e-01 7.4e-03 - 5.70668704030238e-01 7.4e-03 - 5.91022299396154e-01 7.4e-03 - 6.11704971014609e-01 7.4e-03 - 6.32703405878887e-01 7.4e-03 - 6.54007799159681e-01 7.4e-03 - 6.75603313526683e-01 7.4e-03 - 6.97479344035197e-01 7.4e-03 - 7.19619100665882e-01 7.4e-03 - 7.42007863814197e-01 7.4e-03 - 7.64633916307294e-01 7.4e-03 - 7.87480347506928e-01 7.4e-03 - 8.10530974553361e-01 7.4e-03 - 8.33766686857151e-01 7.4e-03 - 8.57171368568559e-01 7.4e-03 - 8.80727606307419e-01 7.4e-03 - 9.04416064906437e-01 7.4e-03 - 9.28217017828997e-01 7.4e-03 - 9.52108466170963e-01 7.4e-03 - 9.76048832000119e-01 7.4e-03 - 1.00000000000000e+00 7.4e-03 diff --git a/examples/RM2/airfoils/NACA_0021.csv b/examples/RM2/airfoils/NACA_0021_AD.csv similarity index 100% rename from examples/RM2/airfoils/NACA_0021.csv rename to examples/RM2/airfoils/NACA_0021_AD.csv diff --git a/examples/RM2/airfoils/NACA_0021_AD.dat b/examples/RM2/airfoils/NACA_0021_AD.dat new file mode 100644 index 00000000..7fd92a8b --- /dev/null +++ b/examples/RM2/airfoils/NACA_0021_AD.dat @@ -0,0 +1,1551 @@ +! ------------ AirfoilInfo v1.01.x Input File ---------------------------------- +! NACA 0018 at Re = 0.01,0.02,0.04,0.08,0.16,0.36,0.70,1,2,5 million +! line +! line +! ------------------------------------------------------------------------------ +DEFAULT InterpOrd - ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] +0.18 RelThickness - ! The non-dimensional thickness of the airfoil (thickness/chord) [only used if UAMod=7] [default=0.2] (-) +1 NonDimArea - ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) +@"NACA_0018_Coords.txt" NumCoords - ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +"NA" BL_file - ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. +7 NumTabs - ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. +! ------------------------------------------------------------------------------ +! data for table +! ------------------------------------------------------------------------------ +0.05 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +3.0 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-3.0 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.4757 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-0.4757 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0214 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +160 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -0.480200000000000 0.405000000000000 0 +-22 -0.334500000000000 0.329000000000000 0 +-20 -0.241400000000000 0.282000000000000 0 +-18 -0.161900000000000 0.238000000000000 0 +-16 -0.0981000000000000 0.196000000000000 0 +-14 -0.0833000000000000 0.158000000000000 0 +-12 -0.166000000000000 0.123000000000000 0 +-10.500 -0.3112 0.12560 0.11631 +-10.250 -0.2843 0.12215 0.11285 +-10.000 -0.3247 0.12282 0.11357 +-9.750 -0.2690 0.11676 0.10748 +-9.500 -0.2967 0.11674 0.10749 +-9.250 -0.2590 0.11173 0.10247 +-9.000 -0.2672 0.11069 0.10145 +-8.750 -0.3659 0.09402 0.08467 +-8.500 -0.3767 0.09022 0.08089 +-8.250 -0.4033 0.08534 0.07605 +-8.000 -0.4715 0.07745 0.06824 +-7.750 -0.4041 0.08041 0.07119 +-7.500 -0.4468 0.07517 0.06603 +-7.250 -0.6906 0.05799 0.04907 +-7.000 -0.8363 0.04920 0.04010 +-6.750 -0.7209 0.05447 0.04562 +-6.500 -0.8240 0.04776 0.03872 +-6.250 -0.7822 0.04914 0.04024 +-6.000 -0.8189 0.04596 0.03692 +-5.750 -0.7958 0.04632 0.03739 +-5.500 -0.8154 0.04402 0.03493 +-5.250 -0.7909 0.04456 0.03561 +-5.000 -0.8085 0.04222 0.03308 +-4.750 -0.7788 0.04326 0.03431 +-4.500 -0.7837 0.04171 0.03266 +-4.250 -0.7645 0.04213 0.03318 +-4.000 -0.7592 0.04136 0.03238 +-3.750 -0.7521 0.04079 0.03179 +-3.500 -0.7355 0.04107 0.03215 +-3.250 -0.7304 0.04029 0.03132 +-3.000 -0.6987 0.04088 0.03197 +-2.750 -0.6416 0.04215 0.03328 +-2.500 -0.5915 0.04298 0.03411 +-2.250 -0.5503 0.04341 0.03453 +-2.000 -0.5136 0.04365 0.03474 +-1.750 -0.4532 0.04526 0.03640 +-1.500 -0.3880 0.04646 0.03760 +-1.250 -0.3540 0.04667 0.03780 +-1.000 -0.3318 0.04665 0.03775 +-0.750 -0.2325 0.04876 0.03989 +-0.500 -0.1461 0.04940 0.04050 +-0.250 -0.1393 0.04928 0.04038 +0.000 0.0000 0.05040 0.04152 +0.250 0.1392 0.04928 0.04038 +0.500 0.1463 0.04939 0.04050 +0.750 0.2325 0.04876 0.03988 +1.000 0.3317 0.04665 0.03775 +1.250 0.3539 0.04667 0.03779 +1.500 0.3878 0.04646 0.03760 +1.750 0.4531 0.04526 0.03639 +2.000 0.5135 0.04365 0.03474 +2.250 0.5504 0.04340 0.03452 +2.500 0.5915 0.04297 0.03410 +2.750 0.6416 0.04214 0.03327 +3.000 0.6987 0.04087 0.03195 +3.250 0.7301 0.04029 0.03132 +3.500 0.7353 0.04106 0.03215 +3.750 0.7520 0.04077 0.03176 +4.000 0.7589 0.04135 0.03237 +4.250 0.7643 0.04211 0.03316 +4.500 0.7834 0.04171 0.03265 +4.750 0.7786 0.04325 0.03430 +5.000 0.8081 0.04222 0.03308 +5.250 0.7906 0.04455 0.03560 +5.500 0.8155 0.04398 0.03490 +5.750 0.7955 0.04631 0.03737 +6.000 0.8190 0.04593 0.03689 +6.250 0.7819 0.04913 0.04023 +6.500 0.8243 0.04773 0.03868 +6.750 0.7216 0.05441 0.04555 +7.000 0.6677 0.05811 0.04924 +7.250 0.6916 0.05791 0.04899 +7.500 0.4474 0.07510 0.06595 +7.750 0.4049 0.08033 0.07110 +8.000 0.4721 0.07739 0.06817 +8.250 0.4039 0.08528 0.07599 +8.500 0.3775 0.09015 0.08082 +8.750 0.3673 0.09391 0.08456 +9.000 0.3997 0.09451 0.08514 +9.250 0.3819 0.09944 0.09006 +9.500 0.3752 0.10386 0.09448 +9.750 0.3820 0.10800 0.09863 +10.250 0.2855 0.12214 0.11284 +10.500 0.3127 0.12563 0.11634 +12 0.166000000000000 0.123000000000000 0 +14 0.0833000000000000 0.158000000000000 0 +16 0.0981000000000000 0.196000000000000 0 +18 0.161900000000000 0.238000000000000 0 +20 0.241400000000000 0.282000000000000 0 +22 0.334500000000000 0.329000000000000 0 +25 0.480200000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 +! ------------------------------------------------------------------------------ +! data for table +! ------------------------------------------------------------------------------ +0.1 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +5.0 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-5.0 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.6566 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-0.6566 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0162 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +194 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -0.666400000000000 0.405000000000000 0 +-22 -0.602300000000000 0.329000000000000 0 +-20 -0.592000000000000 0.282000000000000 0 +-18 -0.609800000000000 0.238000000000000 0 +-16.250 -0.5418 0.17959 0.17300 +-16.000 -0.5218 0.17458 0.16798 +-15.750 -1.0757 0.06945 0.06174 +-15.000 -1.0716 0.06221 0.05443 +-14.750 -1.1181 0.05655 0.04843 +-14.500 -1.1584 0.05230 0.04383 +-14.250 -1.1225 0.05198 0.04374 +-14.000 -1.1217 0.05028 0.04198 +-13.750 -1.1410 0.04769 0.03917 +-13.500 -1.1689 0.04524 0.03640 +-13.250 -1.1295 0.04478 0.03622 +-13.000 -1.1311 0.04343 0.03479 +-12.750 -1.1495 0.04176 0.03290 +-12.500 -1.1393 0.04058 0.03175 +-12.250 -1.1243 0.03993 0.03119 +-12.000 -1.1374 0.03889 0.03002 +-11.750 -1.1599 0.03782 0.02870 +-11.500 -1.1248 0.03722 0.02841 +-11.250 -1.1280 0.03641 0.02754 +-11.000 -1.1446 0.03548 0.02634 +-10.750 -1.1160 0.03489 0.02605 +-10.500 -1.1166 0.03422 0.02531 +-10.250 -1.1202 0.03336 0.02431 +-10.000 -1.1022 0.03292 0.02408 +-9.750 -1.1033 0.03226 0.02330 +-9.500 -1.0943 0.03159 0.02268 +-9.250 -1.0843 0.03117 0.02232 +-9.000 -1.0869 0.03049 0.02143 +-8.750 -1.0682 0.03009 0.02126 +-8.500 -1.0638 0.02958 0.02066 +-8.250 -1.0510 0.02910 0.02027 +-8.000 -1.0410 0.02874 0.01992 +-7.750 -1.0310 0.02826 0.01942 +-7.500 -1.0177 0.02799 0.01923 +-7.250 -1.0080 0.02755 0.01873 +-7.000 -0.9930 0.02735 0.01865 +-6.750 -0.9825 0.02698 0.01820 +-6.500 -0.9668 0.02682 0.01818 +-6.250 -0.9284 0.02666 0.01804 +-6.000 -0.8880 0.02654 0.01784 +-5.750 -0.8396 0.02658 0.01805 +-5.500 -0.8021 0.02640 0.01794 +-5.250 -0.7628 0.02623 0.01776 +-5.000 -0.7209 0.02613 0.01771 +-4.750 -0.6844 0.02600 0.01771 +-4.500 -0.6395 0.02580 0.01754 +-4.250 -0.6102 0.02564 0.01736 +-4.000 -0.5600 0.02548 0.01736 +-3.750 -0.5318 0.02530 0.01722 +-3.500 -0.4845 0.02500 0.01692 +-3.250 -0.4524 0.02493 0.01698 +-3.000 -0.4038 0.02461 0.01674 +-2.750 -0.3715 0.02434 0.01647 +-2.500 -0.3309 0.02410 0.01632 +-2.250 -0.2802 0.02367 0.01597 +-2.000 -0.2618 0.02352 0.01582 +-1.750 -0.2139 0.02312 0.01549 +-1.500 -0.1906 0.02308 0.01553 +-1.250 -0.1507 0.02259 0.01501 +-0.750 -0.0906 0.02245 0.01497 +-0.500 -0.0653 0.02229 0.01480 +-0.250 -0.0304 0.02238 0.01495 +0.000 0.0000 0.02216 0.01468 +0.250 0.0304 0.02238 0.01495 +0.500 0.0653 0.02229 0.01480 +0.750 0.0906 0.02245 0.01496 +1.250 0.1507 0.02260 0.01501 +1.500 0.1906 0.02308 0.01553 +1.750 0.2139 0.02312 0.01549 +2.000 0.2618 0.02352 0.01582 +2.250 0.2802 0.02366 0.01597 +2.500 0.3309 0.02410 0.01632 +2.750 0.3713 0.02434 0.01646 +3.000 0.4037 0.02461 0.01674 +3.250 0.4523 0.02492 0.01698 +3.500 0.4844 0.02500 0.01692 +3.750 0.5316 0.02530 0.01722 +4.000 0.5600 0.02548 0.01735 +4.250 0.6101 0.02563 0.01735 +4.500 0.6395 0.02580 0.01754 +4.750 0.6843 0.02599 0.01771 +5.000 0.7209 0.02612 0.01770 +5.250 0.7627 0.02622 0.01775 +5.500 0.8021 0.02639 0.01793 +5.750 0.8394 0.02657 0.01804 +6.000 0.8879 0.02653 0.01783 +6.250 0.9285 0.02665 0.01803 +6.500 0.9665 0.02681 0.01817 +6.750 0.9822 0.02697 0.01819 +7.000 0.9927 0.02734 0.01864 +7.250 1.0077 0.02754 0.01872 +7.500 1.0174 0.02798 0.01922 +7.750 1.0308 0.02825 0.01941 +8.000 1.0408 0.02873 0.01991 +8.250 1.0508 0.02909 0.02026 +8.500 1.0636 0.02957 0.02064 +8.750 1.0680 0.03008 0.02125 +9.000 1.0866 0.03048 0.02142 +9.250 1.0841 0.03116 0.02231 +9.500 1.0941 0.03159 0.02267 +9.750 1.1032 0.03225 0.02329 +10.000 1.1020 0.03291 0.02406 +10.250 1.1200 0.03335 0.02430 +10.500 1.1165 0.03421 0.02530 +10.750 1.1160 0.03488 0.02604 +11.000 1.1445 0.03547 0.02633 +11.250 1.1281 0.03640 0.02753 +11.500 1.1251 0.03721 0.02840 +11.750 1.1600 0.03781 0.02869 +12.000 1.1377 0.03888 0.03001 +12.250 1.1248 0.03992 0.03118 +12.500 1.1405 0.04056 0.03173 +12.750 1.1499 0.04176 0.03290 +13.000 1.1318 0.04342 0.03479 +13.250 1.1308 0.04476 0.03620 +13.500 1.1694 0.04524 0.03641 +13.750 1.1418 0.04770 0.03918 +14.000 1.1230 0.05026 0.04196 +14.250 1.1250 0.05190 0.04364 +14.500 1.1589 0.05233 0.04386 +14.750 1.1189 0.05658 0.04847 +15.000 1.0729 0.06222 0.05445 +15.250 0.5376 0.16648 0.15990 +16 0.648700000000000 0.196000000000000 0 +18 0.609800000000000 0.238000000000000 0 +20 0.592000000000000 0.282000000000000 0 +22 0.602300000000000 0.329000000000000 0 +25 0.666400000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 +! ------------------------------------------------------------------------------ +! data for table +! ------------------------------------------------------------------------------ +0.2 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +5.0 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-5.0 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.787 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-0.787 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0128 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +221 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -0.886600000000000 0.405000000000000 0 +-22 -0.845300000000000 0.329000000000000 0 +-19.500 -1.1826 0.09047 0.08413 -0.0463 +-19.250 -1.2047 0.08434 0.07776 -0.0489 +-19.000 -1.2278 0.07832 0.07145 -0.0514 +-18.750 -1.2032 0.07853 0.07184 -0.0504 +-18.500 -1.1961 0.07650 0.06982 -0.0509 +-18.250 -1.1992 0.07318 0.06640 -0.0518 +-18.000 -1.2090 0.06910 0.06214 -0.0531 +-17.750 -1.2212 0.06488 0.05769 -0.0542 +-17.500 -1.2022 0.06431 0.05727 -0.0537 +-17.250 -1.1971 0.06218 0.05513 -0.0539 +-17.000 -1.1989 0.05930 0.05214 -0.0544 +-16.750 -1.2067 0.05590 0.04852 -0.0549 +-16.500 -1.1937 0.05462 0.04733 -0.0545 +-16.250 -1.1864 0.05287 0.04559 -0.0544 +-16.000 -1.1842 0.05064 0.04328 -0.0543 +-15.750 -1.1871 0.04802 0.04047 -0.0542 +-15.500 -1.1747 0.04673 0.03926 -0.0537 +-15.250 -1.1677 0.04512 0.03766 -0.0533 +-15.000 -1.1645 0.04322 0.03567 -0.0528 +-14.750 -1.1623 0.04128 0.03358 -0.0521 +-14.500 -1.1497 0.04012 0.03253 -0.0515 +-14.250 -1.1433 0.03864 0.03102 -0.0507 +-14.000 -1.1397 0.03701 0.02926 -0.0497 +-13.750 -1.1282 0.03582 0.02813 -0.0488 +-13.500 -1.1203 0.03459 0.02690 -0.0477 +-13.250 -1.1145 0.03330 0.02552 -0.0464 +-13.000 -1.1045 0.03217 0.02440 -0.0451 +-12.750 -1.0959 0.03114 0.02341 -0.0436 +-12.500 -1.0895 0.03011 0.02230 -0.0418 +-12.250 -1.0801 0.02915 0.02135 -0.0401 +-12.000 -1.0725 0.02831 0.02055 -0.0380 +-11.750 -1.0675 0.02752 0.01969 -0.0354 +-11.500 -1.0603 0.02674 0.01895 -0.0329 +-11.250 -1.0561 0.02610 0.01835 -0.0298 +-11.000 -1.0548 0.02555 0.01774 -0.0261 +-10.750 -1.0521 0.02497 0.01719 -0.0224 +-10.500 -1.0534 0.02452 0.01680 -0.0179 +-10.250 -1.0585 0.02419 0.01642 -0.0126 +-10.000 -1.0652 0.02387 0.01607 -0.0069 +-9.750 -1.0728 0.02355 0.01583 -0.0011 +-9.500 -1.0784 0.02330 0.01558 0.0045 +-9.250 -1.0798 0.02308 0.01526 0.0093 +-9.000 -1.0772 0.02265 0.01495 0.0132 +-8.750 -1.0743 0.02239 0.01469 0.0172 +-8.500 -1.0406 0.02193 0.01426 0.0153 +-8.250 -1.0014 0.02161 0.01391 0.0124 +-8.000 -0.9676 0.02111 0.01352 0.0106 +-7.750 -0.9285 0.02075 0.01314 0.0078 +-7.500 -0.8926 0.02036 0.01282 0.0057 +-7.250 -0.8568 0.01993 0.01244 0.0037 +-7.000 -0.8148 0.01961 0.01207 0.0006 +-6.750 -0.7844 0.01919 0.01179 -0.0002 +-6.500 -0.7448 0.01880 0.01142 -0.0027 +-6.250 -0.7005 0.01845 0.01107 -0.0062 +-6.000 -0.6726 0.01808 0.01081 -0.0063 +-5.750 -0.6312 0.01769 0.01043 -0.0090 +-5.500 -0.5890 0.01729 0.01007 -0.0118 +-5.250 -0.5649 0.01698 0.00984 -0.0110 +-5.000 -0.5284 0.01663 0.00944 -0.0125 +-4.750 -0.5013 0.01630 0.00924 -0.0121 +-4.500 -0.4704 0.01596 0.00889 -0.0124 +-4.250 -0.4429 0.01569 0.00867 -0.0120 +-4.000 -0.4151 0.01537 0.00839 -0.0117 +-3.750 -0.3892 0.01516 0.00815 -0.0109 +-3.500 -0.3617 0.01487 0.00794 -0.0104 +-3.250 -0.3370 0.01470 0.00772 -0.0095 +-3.000 -0.3091 0.01445 0.00752 -0.0090 +-2.750 -0.2848 0.01429 0.00737 -0.0080 +-2.500 -0.2571 0.01412 0.00718 -0.0075 +-2.250 -0.2326 0.01398 0.00709 -0.0066 +-2.000 -0.2073 0.01389 0.00694 -0.0057 +-1.750 -0.1801 0.01375 0.00684 -0.0052 +-1.500 -0.1557 0.01368 0.00675 -0.0043 +-1.250 -0.1288 0.01360 0.00668 -0.0037 +-1.000 -0.1032 0.01353 0.00661 -0.0029 +-0.750 -0.0783 0.01351 0.00657 -0.0020 +-0.250 -0.0264 0.01344 0.00651 -0.0006 +0.000 0.0000 0.01344 0.00652 0.0000 +0.250 0.0264 0.01344 0.00651 0.0006 +0.750 0.0783 0.01351 0.00657 0.0020 +1.000 0.1032 0.01353 0.00661 0.0029 +1.250 0.1288 0.01360 0.00668 0.0037 +1.500 0.1557 0.01368 0.00675 0.0043 +1.750 0.1801 0.01375 0.00684 0.0052 +2.000 0.2073 0.01389 0.00694 0.0057 +2.250 0.2326 0.01398 0.00709 0.0066 +2.500 0.2571 0.01412 0.00718 0.0075 +2.750 0.2848 0.01429 0.00737 0.0080 +3.000 0.3091 0.01444 0.00752 0.0090 +3.250 0.3371 0.01470 0.00772 0.0095 +3.500 0.3617 0.01486 0.00793 0.0104 +3.750 0.3893 0.01516 0.00815 0.0109 +4.000 0.4151 0.01537 0.00839 0.0116 +4.250 0.4429 0.01568 0.00866 0.0120 +4.500 0.4704 0.01595 0.00889 0.0124 +4.750 0.5013 0.01630 0.00924 0.0121 +5.000 0.5284 0.01663 0.00944 0.0125 +5.250 0.5649 0.01697 0.00983 0.0110 +5.500 0.5891 0.01728 0.01007 0.0118 +5.750 0.6313 0.01769 0.01042 0.0090 +6.000 0.6726 0.01808 0.01081 0.0063 +6.250 0.7006 0.01845 0.01106 0.0062 +6.500 0.7449 0.01880 0.01142 0.0027 +6.750 0.7845 0.01919 0.01178 0.0002 +7.000 0.8149 0.01961 0.01207 -0.0006 +7.250 0.8569 0.01992 0.01244 -0.0038 +7.500 0.8926 0.02035 0.01281 -0.0057 +7.750 0.9287 0.02074 0.01313 -0.0079 +8.000 0.9678 0.02110 0.01351 -0.0106 +8.250 1.0017 0.02160 0.01390 -0.0124 +8.500 1.0409 0.02192 0.01425 -0.0153 +8.750 1.0741 0.02238 0.01468 -0.0171 +9.000 1.0770 0.02264 0.01494 -0.0132 +9.250 1.0797 0.02306 0.01524 -0.0093 +9.500 1.0783 0.02329 0.01557 -0.0045 +9.750 1.0729 0.02354 0.01582 0.0010 +10.000 1.0653 0.02386 0.01606 0.0069 +10.250 1.0586 0.02418 0.01641 0.0126 +10.500 1.0536 0.02451 0.01678 0.0179 +10.750 1.0524 0.02495 0.01718 0.0223 +11.000 1.0551 0.02554 0.01772 0.0260 +11.250 1.0565 0.02609 0.01833 0.0297 +11.500 1.0607 0.02673 0.01893 0.0328 +11.750 1.0680 0.02750 0.01967 0.0354 +12.000 1.0731 0.02829 0.02053 0.0379 +12.250 1.0810 0.02913 0.02133 0.0400 +12.500 1.0904 0.03010 0.02228 0.0417 +12.750 1.0969 0.03112 0.02339 0.0435 +13.000 1.1057 0.03215 0.02438 0.0449 +13.250 1.1157 0.03329 0.02550 0.0462 +13.500 1.1216 0.03457 0.02688 0.0475 +13.750 1.1297 0.03580 0.02810 0.0486 +14.000 1.1411 0.03700 0.02924 0.0495 +14.250 1.1448 0.03862 0.03100 0.0505 +14.500 1.1515 0.04009 0.03250 0.0512 +14.750 1.1647 0.04122 0.03351 0.0519 +15.000 1.1663 0.04320 0.03565 0.0525 +15.250 1.1697 0.04508 0.03762 0.0530 +15.500 1.1770 0.04669 0.03921 0.0534 +15.750 1.1888 0.04802 0.04047 0.0539 +16.000 1.1862 0.05062 0.04326 0.0540 +16.250 1.1888 0.05282 0.04554 0.0541 +16.500 1.1965 0.05454 0.04724 0.0542 +16.750 1.2085 0.05592 0.04855 0.0545 +17.000 1.2012 0.05929 0.05213 0.0540 +17.250 1.1998 0.06212 0.05507 0.0536 +17.500 1.2054 0.06420 0.05716 0.0533 +17.750 1.2264 0.06458 0.05736 0.0540 +18.000 1.2113 0.06911 0.06215 0.0527 +18.250 1.2021 0.07314 0.06636 0.0514 +18.500 1.1994 0.07641 0.06972 0.0505 +18.750 1.2073 0.07835 0.07164 0.0501 +19.000 1.2296 0.07842 0.07155 0.0509 +19.250 1.2067 0.08443 0.07786 0.0485 +20 0.839700000000000 0.282000000000000 0 +22 0.845300000000000 0.329000000000000 0 +25 0.886600000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 +! ------------------------------------------------------------------------------ +! data for table +! ------------------------------------------------------------------------------ +0.5 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +6.0 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-6.0 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.9125 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-0.9125 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0101 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +223 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -1.03500000000000 0.405000000000000 0 +-22 -0.994000000000000 0.329000000000000 0 +-20 -0.985800000000000 0.282000000000000 0 +-19.750 -1.2237 0.09201 0.08687 -0.0351 +-19.500 -1.2258 0.08851 0.08331 -0.0364 +-19.250 -1.2282 0.08499 0.07969 -0.0376 +-19.000 -1.2301 0.08156 0.07618 -0.0387 +-18.750 -1.2347 0.07798 0.07260 -0.0397 +-18.500 -1.2386 0.07438 0.06896 -0.0407 +-18.250 -1.2399 0.07113 0.06565 -0.0416 +-18.000 -1.2400 0.06805 0.06249 -0.0425 +-17.750 -1.2408 0.06492 0.05928 -0.0432 +-17.500 -1.2455 0.06147 0.05582 -0.0439 +-17.250 -1.2466 0.05841 0.05273 -0.0445 +-17.000 -1.2451 0.05568 0.04992 -0.0450 +-16.750 -1.2412 0.05321 0.04736 -0.0454 +-16.500 -1.2432 0.05024 0.04437 -0.0457 +-16.250 -1.2435 0.04749 0.04159 -0.0459 +-16.000 -1.2401 0.04515 0.03921 -0.0461 +-15.750 -1.2336 0.04313 0.03711 -0.0461 +-15.500 -1.2310 0.04083 0.03476 -0.0460 +-15.250 -1.2290 0.03853 0.03245 -0.0458 +-15.000 -1.2228 0.03667 0.03056 -0.0455 +-14.750 -1.2129 0.03516 0.02898 -0.0452 +-14.500 -1.2091 0.03322 0.02702 -0.0446 +-14.250 -1.2032 0.03152 0.02530 -0.0439 +-14.000 -1.1933 0.03017 0.02392 -0.0433 +-13.750 -1.1831 0.02890 0.02260 -0.0425 +-13.500 -1.1771 0.02739 0.02110 -0.0414 +-13.250 -1.1671 0.02624 0.01993 -0.0404 +-13.000 -1.1535 0.02537 0.01900 -0.0394 +-12.750 -1.1475 0.02410 0.01775 -0.0378 +-12.500 -1.1375 0.02317 0.01682 -0.0363 +-12.250 -1.1246 0.02250 0.01610 -0.0348 +-12.000 -1.1200 0.02154 0.01518 -0.0323 +-11.750 -1.1136 0.02086 0.01450 -0.0296 +-11.500 -1.1058 0.02039 0.01399 -0.0268 +-11.250 -1.1078 0.01975 0.01338 -0.0225 +-11.000 -1.1107 0.01929 0.01293 -0.0177 +-10.750 -1.1141 0.01898 0.01260 -0.0127 +-10.500 -1.1224 0.01870 0.01229 -0.0067 +-10.250 -1.0934 0.01806 0.01171 -0.0080 +-10.000 -1.0611 0.01758 0.01122 -0.0096 +-9.750 -1.0285 0.01705 0.01074 -0.0113 +-9.500 -0.9983 0.01656 0.01028 -0.0124 +-9.250 -0.9668 0.01609 0.00984 -0.0138 +-9.000 -0.9330 0.01561 0.00939 -0.0155 +-8.750 -0.8959 0.01519 0.00899 -0.0178 +-8.500 -0.8643 0.01471 0.00856 -0.0190 +-8.250 -0.8319 0.01436 0.00821 -0.0202 +-8.000 -0.8001 0.01385 0.00778 -0.0214 +-7.750 -0.7692 0.01351 0.00745 -0.0222 +-7.500 -0.7466 0.01314 0.00713 -0.0212 +-7.250 -0.7182 0.01282 0.00681 -0.0214 +-7.000 -0.6987 0.01251 0.00655 -0.0197 +-6.750 -0.6738 0.01225 0.00627 -0.0190 +-6.500 -0.6532 0.01198 0.00604 -0.0175 +-6.250 -0.6292 0.01176 0.00580 -0.0166 +-6.000 -0.6071 0.01151 0.00558 -0.0154 +-5.750 -0.5831 0.01132 0.00538 -0.0145 +-5.500 -0.5596 0.01110 0.00517 -0.0135 +-5.250 -0.5355 0.01093 0.00500 -0.0127 +-5.000 -0.5109 0.01076 0.00481 -0.0119 +-4.750 -0.4866 0.01060 0.00467 -0.0111 +-4.500 -0.4615 0.01047 0.00452 -0.0104 +-4.250 -0.4368 0.01033 0.00437 -0.0096 +-4.000 -0.4113 0.01023 0.00425 -0.0090 +-3.750 -0.3865 0.01010 0.00411 -0.0083 +-3.500 -0.3605 0.01003 0.00401 -0.0078 +-3.250 -0.3357 0.00991 0.00391 -0.0071 +-2.750 -0.2845 0.00976 0.00373 -0.0059 +-2.500 -0.2583 0.00972 0.00365 -0.0054 +-2.250 -0.2331 0.00965 0.00358 -0.0048 +-2.000 -0.2069 0.00960 0.00352 -0.0043 +-1.750 -0.1814 0.00956 0.00346 -0.0037 +-1.500 -0.1554 0.00952 0.00342 -0.0032 +-1.250 -0.1295 0.00949 0.00338 -0.0027 +-1.000 -0.1040 0.00947 0.00334 -0.0020 +-0.750 -0.0774 0.00946 0.00332 -0.0016 +-0.500 -0.0521 0.00943 0.00331 -0.0010 +-0.250 -0.0258 0.00944 0.00329 -0.0006 +0.000 0.0000 0.00942 0.00329 0.0000 +0.250 0.0258 0.00944 0.00329 0.0006 +0.500 0.0521 0.00943 0.00331 0.0010 +0.750 0.0774 0.00946 0.00332 0.0016 +1.000 0.1040 0.00947 0.00334 0.0020 +1.250 0.1295 0.00949 0.00338 0.0027 +1.500 0.1555 0.00952 0.00341 0.0032 +1.750 0.1815 0.00956 0.00346 0.0037 +2.000 0.2069 0.00960 0.00352 0.0043 +2.250 0.2331 0.00965 0.00358 0.0048 +2.500 0.2583 0.00972 0.00365 0.0054 +2.750 0.2845 0.00976 0.00373 0.0059 +3.250 0.3357 0.00991 0.00391 0.0071 +3.500 0.3606 0.01003 0.00401 0.0078 +3.750 0.3866 0.01010 0.00411 0.0083 +4.000 0.4114 0.01023 0.00425 0.0090 +4.250 0.4369 0.01033 0.00437 0.0096 +4.500 0.4616 0.01047 0.00452 0.0104 +4.750 0.4867 0.01060 0.00467 0.0111 +5.000 0.5110 0.01076 0.00481 0.0119 +5.250 0.5356 0.01093 0.00500 0.0127 +5.500 0.5598 0.01110 0.00517 0.0135 +5.750 0.5833 0.01132 0.00538 0.0145 +6.000 0.6073 0.01151 0.00558 0.0153 +6.250 0.6294 0.01176 0.00580 0.0166 +6.500 0.6535 0.01198 0.00604 0.0174 +6.750 0.6741 0.01225 0.00627 0.0189 +7.000 0.6990 0.01251 0.00655 0.0196 +7.250 0.7185 0.01282 0.00681 0.0213 +7.500 0.7469 0.01314 0.00712 0.0212 +7.750 0.7695 0.01351 0.00744 0.0221 +8.000 0.8005 0.01385 0.00778 0.0213 +8.250 0.8323 0.01435 0.00821 0.0201 +8.500 0.8646 0.01470 0.00856 0.0190 +8.750 0.8964 0.01519 0.00899 0.0177 +9.000 0.9335 0.01561 0.00939 0.0154 +9.250 0.9673 0.01609 0.00983 0.0136 +9.500 0.9988 0.01656 0.01027 0.0123 +9.750 1.0292 0.01704 0.01073 0.0112 +10.000 1.0618 0.01757 0.01121 0.0095 +10.250 1.0941 0.01805 0.01169 0.0078 +10.500 1.1224 0.01868 0.01227 0.0067 +10.750 1.1141 0.01897 0.01258 0.0127 +11.000 1.1108 0.01927 0.01291 0.0177 +11.250 1.1079 0.01973 0.01335 0.0225 +11.500 1.1062 0.02037 0.01396 0.0267 +11.750 1.1141 0.02084 0.01448 0.0295 +12.000 1.1207 0.02152 0.01515 0.0322 +12.250 1.1256 0.02247 0.01607 0.0346 +12.500 1.1386 0.02315 0.01680 0.0361 +12.750 1.1487 0.02408 0.01773 0.0376 +13.000 1.1550 0.02533 0.01896 0.0392 +13.250 1.1687 0.02620 0.01989 0.0401 +13.500 1.1787 0.02736 0.02107 0.0412 +13.750 1.1847 0.02888 0.02257 0.0423 +14.000 1.1953 0.03012 0.02387 0.0430 +14.250 1.2052 0.03147 0.02526 0.0436 +14.500 1.2111 0.03319 0.02698 0.0443 +14.750 1.2153 0.03510 0.02891 0.0449 +15.000 1.2252 0.03660 0.03049 0.0452 +15.250 1.2315 0.03847 0.03238 0.0454 +15.500 1.2333 0.04078 0.03471 0.0456 +15.750 1.2364 0.04305 0.03702 0.0457 +16.000 1.2429 0.04507 0.03912 0.0457 +16.250 1.2463 0.04742 0.04151 0.0456 +16.500 1.2460 0.05018 0.04430 0.0453 +16.750 1.2446 0.05309 0.04724 0.0450 +17.000 1.2484 0.05558 0.04982 0.0446 +17.250 1.2499 0.05832 0.05263 0.0441 +17.500 1.2487 0.06139 0.05573 0.0435 +17.750 1.2439 0.06486 0.05921 0.0428 +18.000 1.2436 0.06794 0.06238 0.0420 +18.250 1.2437 0.07102 0.06554 0.0412 +18.500 1.2422 0.07429 0.06887 0.0402 +18.750 1.2382 0.07790 0.07251 0.0392 +19.000 1.2338 0.08146 0.07607 0.0382 +19.250 1.2320 0.08490 0.07961 0.0371 +20 0.985800000000000 0.282000000000000 0 +22 0.994000000000000 0.329000000000000 0 +25 1.03500000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 +! ------------------------------------------------------------------------------ +! data for table +! ------------------------------------------------------------------------------ +1.0 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +17.801185316865297 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-17.801185316865297 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.0573 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.0573 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0082 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +221 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -1.10180000000000 0.405000000000000 0 +-22 -1.06440000000000 0.329000000000000 0 +-20 -1.05540000000000 0.282000000000000 0 +-19.750 -1.3432 0.07827 0.07364 -0.0368 +-19.500 -1.3520 0.07412 0.06942 -0.0380 +-19.250 -1.3588 0.07026 0.06549 -0.0390 +-19.000 -1.3630 0.06671 0.06187 -0.0399 +-18.750 -1.3640 0.06359 0.05867 -0.0407 +-18.500 -1.3727 0.05963 0.05465 -0.0415 +-18.250 -1.3785 0.05608 0.05105 -0.0422 +-18.000 -1.3809 0.05296 0.04787 -0.0427 +-17.750 -1.3805 0.05018 0.04503 -0.0430 +-17.500 -1.3775 0.04772 0.04250 -0.0433 +-17.250 -1.3782 0.04492 0.03965 -0.0435 +-17.000 -1.3782 0.04225 0.03694 -0.0436 +-16.750 -1.3750 0.03997 0.03462 -0.0436 +-16.500 -1.3687 0.03803 0.03263 -0.0435 +-16.250 -1.3613 0.03623 0.03077 -0.0433 +-16.000 -1.3583 0.03408 0.02860 -0.0429 +-15.750 -1.3521 0.03228 0.02677 -0.0425 +-15.500 -1.3428 0.03079 0.02525 -0.0420 +-15.250 -1.3326 0.02943 0.02384 -0.0415 +-15.000 -1.3257 0.02784 0.02225 -0.0407 +-14.750 -1.3161 0.02652 0.02091 -0.0399 +-14.500 -1.3036 0.02546 0.01981 -0.0392 +-14.250 -1.2929 0.02431 0.01864 -0.0383 +-14.000 -1.2826 0.02319 0.01751 -0.0372 +-13.750 -1.2700 0.02226 0.01657 -0.0361 +-13.500 -1.2556 0.02150 0.01577 -0.0351 +-13.250 -1.2456 0.02055 0.01483 -0.0335 +-13.000 -1.2336 0.01979 0.01407 -0.0319 +-12.750 -1.2204 0.01920 0.01346 -0.0303 +-12.500 -1.2131 0.01851 0.01277 -0.0277 +-12.250 -1.2076 0.01796 0.01222 -0.0245 +-12.000 -1.2041 0.01754 0.01179 -0.0208 +-11.750 -1.2064 0.01719 0.01142 -0.0159 +-11.500 -1.1882 0.01662 0.01088 -0.0150 +-11.250 -1.1585 0.01613 0.01039 -0.0162 +-11.000 -1.1294 0.01557 0.00986 -0.0173 +-10.750 -1.0982 0.01510 0.00941 -0.0186 +-10.500 -1.0669 0.01459 0.00894 -0.0201 +-10.250 -1.0385 0.01417 0.00853 -0.0207 +-10.000 -1.0087 0.01368 0.00809 -0.0217 +-9.750 -0.9774 0.01330 0.00772 -0.0228 +-9.500 -0.9478 0.01283 0.00731 -0.0237 +-9.250 -0.9247 0.01253 0.00701 -0.0229 +-9.000 -0.9015 0.01212 0.00664 -0.0222 +-8.750 -0.8817 0.01186 0.00638 -0.0207 +-8.500 -0.8619 0.01154 0.00607 -0.0192 +-8.250 -0.8432 0.01131 0.00585 -0.0174 +-8.000 -0.8229 0.01107 0.00561 -0.0159 +-7.750 -0.8009 0.01083 0.00538 -0.0147 +-7.500 -0.7780 0.01061 0.00516 -0.0137 +-7.250 -0.7551 0.01040 0.00495 -0.0128 +-7.000 -0.7311 0.01020 0.00476 -0.0120 +-6.750 -0.7074 0.01001 0.00456 -0.0111 +-6.500 -0.6827 0.00983 0.00438 -0.0105 +-6.250 -0.6583 0.00966 0.00420 -0.0098 +-6.000 -0.6331 0.00950 0.00405 -0.0092 +-5.750 -0.6081 0.00935 0.00389 -0.0086 +-5.500 -0.5827 0.00922 0.00375 -0.0080 +-5.250 -0.5571 0.00908 0.00361 -0.0075 +-5.000 -0.5317 0.00897 0.00348 -0.0070 +-4.750 -0.5056 0.00885 0.00336 -0.0065 +-4.500 -0.4799 0.00874 0.00324 -0.0061 +-4.250 -0.4538 0.00866 0.00314 -0.0056 +-4.000 -0.4278 0.00855 0.00304 -0.0052 +-3.750 -0.4013 0.00849 0.00296 -0.0048 +-3.500 -0.3754 0.00839 0.00286 -0.0044 +-3.250 -0.3483 0.00835 0.00280 -0.0041 +-3.000 -0.3226 0.00827 0.00272 -0.0036 +-2.500 -0.2691 0.00816 0.00260 -0.0029 +-2.250 -0.2421 0.00814 0.00255 -0.0027 +-2.000 -0.2155 0.00807 0.00250 -0.0023 +-1.750 -0.1886 0.00807 0.00246 -0.0020 +-1.500 -0.1618 0.00801 0.00242 -0.0017 +-1.250 -0.1347 0.00800 0.00240 -0.0015 +-1.000 -0.1080 0.00798 0.00237 -0.0011 +-0.750 -0.0808 0.00796 0.00235 -0.0009 +-0.250 -0.0269 0.00793 0.00233 -0.0003 +0.000 0.0000 0.00796 0.00233 0.0000 +0.250 0.0269 0.00793 0.00233 0.0003 +0.750 0.0808 0.00796 0.00235 0.0009 +1.000 0.1080 0.00798 0.00237 0.0011 +1.250 0.1347 0.00800 0.00240 0.0015 +1.500 0.1618 0.00801 0.00242 0.0017 +1.750 0.1886 0.00807 0.00246 0.0020 +2.000 0.2155 0.00807 0.00250 0.0023 +2.250 0.2421 0.00814 0.00255 0.0027 +2.500 0.2692 0.00816 0.00260 0.0029 +3.000 0.3227 0.00827 0.00272 0.0036 +3.250 0.3483 0.00835 0.00280 0.0041 +3.500 0.3754 0.00839 0.00286 0.0043 +3.750 0.4014 0.00849 0.00296 0.0048 +4.000 0.4279 0.00855 0.00304 0.0052 +4.250 0.4539 0.00866 0.00314 0.0056 +4.500 0.4800 0.00874 0.00324 0.0060 +4.750 0.5058 0.00885 0.00336 0.0065 +5.000 0.5318 0.00897 0.00348 0.0069 +5.250 0.5573 0.00908 0.00361 0.0075 +5.500 0.5829 0.00922 0.00375 0.0080 +5.750 0.6083 0.00935 0.00389 0.0085 +6.000 0.6333 0.00950 0.00405 0.0091 +6.250 0.6585 0.00966 0.00420 0.0097 +6.500 0.6829 0.00983 0.00438 0.0104 +6.750 0.7076 0.01001 0.00456 0.0111 +7.000 0.7314 0.01020 0.00476 0.0119 +7.250 0.7554 0.01040 0.00495 0.0127 +7.500 0.7784 0.01061 0.00516 0.0137 +7.750 0.8013 0.01083 0.00538 0.0146 +8.000 0.8233 0.01107 0.00561 0.0158 +8.250 0.8438 0.01131 0.00585 0.0172 +8.500 0.8625 0.01154 0.00607 0.0191 +8.750 0.8823 0.01186 0.00638 0.0206 +9.000 0.9021 0.01212 0.00664 0.0221 +9.250 0.9253 0.01252 0.00700 0.0228 +9.500 0.9483 0.01283 0.00730 0.0236 +9.750 0.9780 0.01329 0.00772 0.0227 +10.000 1.0093 0.01368 0.00808 0.0216 +10.250 1.0390 0.01416 0.00853 0.0206 +10.500 1.0676 0.01458 0.00893 0.0199 +10.750 1.0990 0.01510 0.00940 0.0185 +11.000 1.1302 0.01556 0.00985 0.0171 +11.250 1.1594 0.01612 0.01038 0.0160 +11.500 1.1891 0.01661 0.01086 0.0149 +11.750 1.2063 0.01717 0.01140 0.0159 +12.000 1.2043 0.01752 0.01177 0.0208 +12.250 1.2080 0.01794 0.01220 0.0245 +12.500 1.2137 0.01849 0.01275 0.0276 +12.750 1.2213 0.01918 0.01343 0.0302 +13.000 1.2347 0.01977 0.01405 0.0318 +13.250 1.2468 0.02053 0.01481 0.0333 +13.500 1.2570 0.02148 0.01575 0.0348 +13.750 1.2716 0.02223 0.01654 0.0358 +14.000 1.2842 0.02316 0.01748 0.0369 +14.250 1.2946 0.02428 0.01861 0.0380 +14.500 1.3057 0.02541 0.01976 0.0389 +14.750 1.3182 0.02648 0.02086 0.0396 +15.000 1.3279 0.02780 0.02220 0.0404 +15.250 1.3347 0.02939 0.02380 0.0412 +15.500 1.3454 0.03072 0.02518 0.0417 +15.750 1.3546 0.03222 0.02671 0.0421 +16.000 1.3609 0.03402 0.02854 0.0425 +16.250 1.3639 0.03617 0.03071 0.0429 +16.500 1.3719 0.03793 0.03253 0.0431 +16.750 1.3781 0.03987 0.03452 0.0432 +17.000 1.3814 0.04216 0.03685 0.0432 +17.250 1.3813 0.04484 0.03957 0.0431 +17.500 1.3813 0.04758 0.04236 0.0429 +17.750 1.3843 0.05004 0.04489 0.0426 +18.000 1.3848 0.05282 0.04773 0.0422 +18.250 1.3824 0.05595 0.05091 0.0417 +18.500 1.3766 0.05951 0.05452 0.0410 +18.750 1.3688 0.06336 0.05844 0.0402 +19.000 1.3675 0.06653 0.06168 0.0394 +19.250 1.3631 0.07010 0.06533 0.0385 +20 1.05540000000000 0.282000000000000 0 +22 1.06440000000000 0.329000000000000 0 +25 1.10180000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 +! ------------------------------------------------------------------------------ +! data for table +! ------------------------------------------------------------------------------ +2.0 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +20.027374578257152 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-20.027374578257152 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.151 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.151 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0077 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +105 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +-1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 +-1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 +-1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 +-1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 +-1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 +-1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 +-1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 +-1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 +-1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 +-1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 +-1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 +-1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 +-1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 +-1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 +-1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 +-1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 +-9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 +-9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 +-8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 +-8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 +-7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 +-7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 +-6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 +-6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 +-5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 +-5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 +-4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 +-4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 +-3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 +-3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 +-2.50000000e+01 -1.14680000e+00 4.05000000e-01 0.00000000e+00 +-2.20000000e+01 -1.11270000e+00 3.29000000e-01 0.00000000e+00 +-2.00000000e+01 -1.11720000e+00 2.82000000e-01 0.00000000e+00 +-1.80000000e+01 -1.13830000e+00 2.38000000e-01 0.00000000e+00 +-1.70000000e+01 -1.15500000e+00 1.20000000e-01 0.00000000e+00 +-1.60000000e+01 -1.16950000e+00 2.40000000e-02 0.00000000e+00 +-1.50000000e+01 -1.18130000e+00 2.18000000e-02 0.00000000e+00 +-1.40000000e+01 -1.18130000e+00 1.97000000e-02 0.00000000e+00 +-1.30000000e+01 -1.16620000e+00 1.79000000e-02 0.00000000e+00 +-1.20000000e+01 -1.12960000e+00 1.63000000e-02 0.00000000e+00 +-1.10000000e+01 -1.07720000e+00 1.48000000e-02 0.00000000e+00 +-1.00000000e+01 -1.01110000e+00 1.34000000e-02 0.00000000e+00 +-9.00000000e+00 -9.31400000e-01 1.22000000e-02 0.00000000e+00 +-8.00000000e+00 -8.43900000e-01 1.11000000e-02 0.00000000e+00 +-7.00000000e+00 -7.44900000e-01 1.01000000e-02 0.00000000e+00 +-6.00000000e+00 -6.60000000e-01 9.30000000e-03 0.00000000e+00 +-5.00000000e+00 -5.50000000e-01 8.70000000e-03 0.00000000e+00 +-4.00000000e+00 -4.40000000e-01 8.40000000e-03 0.00000000e+00 +-3.00000000e+00 -3.30000000e-01 8.00000000e-03 0.00000000e+00 +-2.00000000e+00 -2.20000000e-01 7.80000000e-03 0.00000000e+00 +-1.00000000e+00 -1.10000000e-01 7.70000000e-03 0.00000000e+00 + 0.00000000e+00 0.00000000e+00 7.70000000e-03 0.00000000e+00 + 1.00000000e+00 1.10000000e-01 7.70000000e-03 0.00000000e+00 + 2.00000000e+00 2.20000000e-01 7.80000000e-03 0.00000000e+00 + 3.00000000e+00 3.30000000e-01 8.00000000e-03 0.00000000e+00 + 4.00000000e+00 4.40000000e-01 8.40000000e-03 0.00000000e+00 + 5.00000000e+00 5.50000000e-01 8.70000000e-03 0.00000000e+00 + 6.00000000e+00 6.60000000e-01 9.30000000e-03 0.00000000e+00 + 7.00000000e+00 7.44900000e-01 1.01000000e-02 0.00000000e+00 + 8.00000000e+00 8.43900000e-01 1.11000000e-02 0.00000000e+00 + 9.00000000e+00 9.31400000e-01 1.22000000e-02 0.00000000e+00 + 1.00000000e+01 1.01110000e+00 1.34000000e-02 0.00000000e+00 + 1.10000000e+01 1.07720000e+00 1.48000000e-02 0.00000000e+00 + 1.20000000e+01 1.12960000e+00 1.63000000e-02 0.00000000e+00 + 1.30000000e+01 1.16620000e+00 1.79000000e-02 0.00000000e+00 + 1.40000000e+01 1.18130000e+00 1.97000000e-02 0.00000000e+00 + 1.50000000e+01 1.18130000e+00 2.18000000e-02 0.00000000e+00 + 1.60000000e+01 1.16950000e+00 2.40000000e-02 0.00000000e+00 + 1.70000000e+01 1.15500000e+00 1.20000000e-01 0.00000000e+00 + 1.80000000e+01 1.13830000e+00 2.38000000e-01 0.00000000e+00 + 2.00000000e+01 1.11720000e+00 2.82000000e-01 0.00000000e+00 + 2.20000000e+01 1.11270000e+00 3.29000000e-01 0.00000000e+00 + 2.50000000e+01 1.14680000e+00 4.05000000e-01 0.00000000e+00 + 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 + 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 + 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 + 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 + 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 + 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 + 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 + 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 + 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 + 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 + 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 + 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 + 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 + 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 + 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 + 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 + 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 + 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 + 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 + 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 + 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 + 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 + 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 + 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 + 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 + 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 + 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 + 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 + 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 + 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 + 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +! ------------------------------------------------------------------------------ +! data for table +! ------------------------------------------------------------------------------ +5.0 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +23.403123375221707 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-23.403123375221707 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.2617 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.2617 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0073 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +107 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +-1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 +-1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 +-1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 +-1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 +-1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 +-1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 +-1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 +-1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 +-1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 +-1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 +-1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 +-1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 +-1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 +-1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 +-1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 +-1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 +-9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 +-9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 +-8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 +-8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 +-7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 +-7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 +-6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 +-6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 +-5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 +-5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 +-4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 +-4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 +-3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 +-3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 +-2.50000000e+01 -1.29250000e+00 4.05000000e-01 0.00000000e+00 +-2.20000000e+01 -1.27140000e+00 3.29000000e-01 0.00000000e+00 +-2.00000000e+01 -1.27680000e+00 2.82000000e-01 0.00000000e+00 +-1.90000000e+01 -1.28530000e+00 1.40000000e-01 0.00000000e+00 +-1.80000000e+01 -1.29600000e+00 2.44000000e-02 0.00000000e+00 +-1.70000000e+01 -1.30380000e+00 2.23000000e-02 0.00000000e+00 +-1.60000000e+01 -1.30670000e+00 2.03000000e-02 0.00000000e+00 +-1.50000000e+01 -1.30040000e+00 1.85000000e-02 0.00000000e+00 +-1.40000000e+01 -1.28080000e+00 1.68000000e-02 0.00000000e+00 +-1.30000000e+01 -1.24300000e+00 1.53000000e-02 0.00000000e+00 +-1.20000000e+01 -1.18840000e+00 1.40000000e-02 0.00000000e+00 +-1.10000000e+01 -1.12110000e+00 1.28000000e-02 0.00000000e+00 +-1.00000000e+01 -1.04040000e+00 1.17000000e-02 0.00000000e+00 +-9.00000000e+00 -9.52500000e-01 1.08000000e-02 0.00000000e+00 +-8.00000000e+00 -8.53800000e-01 1.00000000e-02 0.00000000e+00 +-7.00000000e+00 -7.70000000e-01 9.30000000e-03 0.00000000e+00 +-6.00000000e+00 -6.60000000e-01 8.70000000e-03 0.00000000e+00 +-5.00000000e+00 -5.50000000e-01 8.30000000e-03 0.00000000e+00 +-4.00000000e+00 -4.40000000e-01 7.90000000e-03 0.00000000e+00 +-3.00000000e+00 -3.30000000e-01 7.70000000e-03 0.00000000e+00 +-2.00000000e+00 -2.20000000e-01 7.50000000e-03 0.00000000e+00 +-1.00000000e+00 -1.10000000e-01 7.30000000e-03 0.00000000e+00 + 0.00000000e+00 0.00000000e+00 7.30000000e-03 0.00000000e+00 + 1.00000000e+00 1.10000000e-01 7.30000000e-03 0.00000000e+00 + 2.00000000e+00 2.20000000e-01 7.50000000e-03 0.00000000e+00 + 3.00000000e+00 3.30000000e-01 7.70000000e-03 0.00000000e+00 + 4.00000000e+00 4.40000000e-01 7.90000000e-03 0.00000000e+00 + 5.00000000e+00 5.50000000e-01 8.30000000e-03 0.00000000e+00 + 6.00000000e+00 6.60000000e-01 8.70000000e-03 0.00000000e+00 + 7.00000000e+00 7.70000000e-01 9.30000000e-03 0.00000000e+00 + 8.00000000e+00 8.53800000e-01 1.00000000e-02 0.00000000e+00 + 9.00000000e+00 9.52500000e-01 1.08000000e-02 0.00000000e+00 + 1.00000000e+01 1.04040000e+00 1.17000000e-02 0.00000000e+00 + 1.10000000e+01 1.12110000e+00 1.28000000e-02 0.00000000e+00 + 1.20000000e+01 1.18840000e+00 1.40000000e-02 0.00000000e+00 + 1.30000000e+01 1.24300000e+00 1.53000000e-02 0.00000000e+00 + 1.40000000e+01 1.28080000e+00 1.68000000e-02 0.00000000e+00 + 1.50000000e+01 1.30040000e+00 1.85000000e-02 0.00000000e+00 + 1.60000000e+01 1.30670000e+00 2.03000000e-02 0.00000000e+00 + 1.70000000e+01 1.30380000e+00 2.23000000e-02 0.00000000e+00 + 1.80000000e+01 1.29600000e+00 2.44000000e-02 0.00000000e+00 + 1.90000000e+01 1.28530000e+00 1.40000000e-01 0.00000000e+00 + 2.00000000e+01 1.27680000e+00 2.82000000e-01 0.00000000e+00 + 2.20000000e+01 1.27140000e+00 3.29000000e-01 0.00000000e+00 + 2.50000000e+01 1.29250000e+00 4.05000000e-01 0.00000000e+00 + 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 + 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 + 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 + 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 + 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 + 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 + 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 + 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 + 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 + 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 + 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 + 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 + 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 + 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 + 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 + 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 + 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 + 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 + 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 + 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 + 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 + 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 + 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 + 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 + 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 + 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 + 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 + 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 + 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 + 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 + 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 + diff --git a/examples/RM2/airfoils/NACA_0021_DMS.csv b/examples/RM2/airfoils/NACA_0021_DMS.csv new file mode 100644 index 00000000..2e840158 --- /dev/null +++ b/examples/RM2/airfoils/NACA_0021_DMS.csv @@ -0,0 +1,34 @@ +100,0.0 +95,-1.412 +90,-2.534 +80,-4.591 +70,-6.412 +60,-7.986 +50,-9.265 +40,-10.156 +30,-10.504 +25,-10.397 +20,-10.04 +15,-9.354 +10,-8.195 +7.5,-7.35 +5,-6.221 +2.5,-4.576 +1.25,-3.315 +0,0 +1.25,3.315 +2.5,4.576 +5,6.221 +7.5,7.35 +10,8.195 +15,9.354 +20,10.04 +25,10.397 +30,10.504 +40,10.156 +50,9.265 +60,7.986 +70,6.412 +80,4.591 +90,2.534 +95,1.412 \ No newline at end of file diff --git a/examples/RM2/airfoils/NACA_0021.dat b/examples/RM2/airfoils/NACA_0021_DMS.dat similarity index 100% rename from examples/RM2/airfoils/NACA_0021.dat rename to examples/RM2/airfoils/NACA_0021_DMS.dat diff --git a/examples/RM2/modeling_options_OWENS_RM2.yml b/examples/RM2/modeling_options_OWENS_RM2.yml index 553c0a93..5f19ecf2 100644 --- a/examples/RM2/modeling_options_OWENS_RM2.yml +++ b/examples/RM2/modeling_options_OWENS_RM2.yml @@ -1,6 +1,6 @@ OWENS_Options: analysisType: "Unsteady" # Unsteady, DLC, Campbell, todo: steady, flutter may be re-activated in the future. - AeroModel: "DMS" # OWENSAero model "DMS" for double multiple streamtube or "AC" for actuator cylinder, or "AD" for aerodyn + AeroModel: "AD" # OWENSAero model "DMS" for double multiple streamtube or "AC" for actuator cylinder, or "AD" for aerodyn structuralModel: "GX" #Structural models available: TNB full timoshenko beam elements with time newmark beta time stepping, ROM reduced order modal model of the timoshenko elements, GX with GXBeam's methods for geometrically exact beam theory and more efficient methods and time stepping controlStrategy: "prescribedRPM" # should be in WindIO?- yes, numTS: 10 # number of time steps TODO: change to sim time and make this derived diff --git a/examples/SNL17m/GuyWire_Verification.jl b/examples/SNL17m/GuyWire_Verification.jl index 4c4c6443..a5951270 100644 --- a/examples/SNL17m/GuyWire_Verification.jl +++ b/examples/SNL17m/GuyWire_Verification.jl @@ -52,12 +52,12 @@ Blade_Height = 17.1 Blade_Radius = 17.1/2 numTS = 2000 delta_t = 0.05 -NuMad_geom_xlscsv_file_twr = "$(path)/data/NuMAD_34m_TowerGeom.csv" -NuMad_mat_xlscsv_file_twr = "$(path)/data/NuMAD_34m_TowerMaterials.csv" -NuMad_geom_xlscsv_file_bld = "$(path)/data/NuMAD_SNL34mGeomBlades.csv" -NuMad_mat_xlscsv_file_bld = "$(path)/data/NuMAD_SNL34mMaterials.csv" -NuMad_geom_xlscsv_file_strut = "$(path)/data/NuMAD_SNL34mGeomStruts.csv" -NuMad_mat_xlscsv_file_strut = "$(path)/data/NuMAD_SNL34mMaterials.csv" +NuMad_geom_xlscsv_file_twr = "$(path)/data/tower_NuMAD.csv" +NuMad_mat_xlscsv_file_twr = "$(path)/data/materials_NuMAD.csv" +NuMad_geom_xlscsv_file_bld = "$(path)/data/blades_NuMAD.csv" +NuMad_mat_xlscsv_file_bld = "$(path)/data/materials_NuMAD.csv" +NuMad_geom_xlscsv_file_strut = "$(path)/data/struts_NuMAD.csv" +NuMad_mat_xlscsv_file_strut = "$(path)/data/materials_NuMAD.csv" adi_lib = nothing adi_rootname = "$(path)/SNL34m" @@ -134,7 +134,8 @@ mass_breakout_blds,mass_breakout_twr,system, assembly, sections,_,_,custom_mesh_ cables_connected_to_blade_base = true, angularOffset = pi/2, custommesh = create_mesh, - meshtype = turbineType) + meshtype = turbineType, + VTKmeshfilename = "$path/VTK/17m_init") PyPlot.figure() for icon = 1:length(mymesh.conn[:,1]) @@ -162,9 +163,19 @@ PyPlot.axis("equal") g2ground_idx,g2t_idx = custom_mesh_outputs guy_stiff = myel.props[end].EA[2] -pretension = 44000.0 #N +guy_mass = myel.props[end].rhoA[2] +# guy mass is 3.08 kg/m +pretension = 440000.0 * 0 #N lengthguy = sqrt((towerHeight+Blade_Height)^2 + 36.4^2) -predeformation = pretension/guy_stiff*lengthguy + +guyanchor_radius = 36.4 +Height = 0.99*(Blade_Height+towerHeight) +thetaD_guy = atand(guyanchor_radius/Height) +pretension_Z = pretension/cosd(thetaD_guy) + +predeformation = pretension_Z/guy_stiff*lengthguy + + # node, dof, bc @@ -236,6 +247,10 @@ freqGX = [freq2[:,i] for i=1:2:FEAinputs.numModes-6-2] NperRevLines = 8 rotSpdArrayRPM = LinRange(0.0, 2.0, 2) # int + + +guy_analytical_1stHz = 1/(2*lengthguy)*sqrt(pretension/guy_mass) + PyPlot.figure() #plot per rev lines for i=1:NperRevLines diff --git a/examples/SNL17m/airfoils/Airfoils.txt b/examples/SNL17m/airfoils/Airfoils.txt deleted file mode 100644 index 516c3ad3..00000000 --- a/examples/SNL17m/airfoils/Airfoils.txt +++ /dev/null @@ -1,39 +0,0 @@ -04/10/97 - -Coordinates for the SNL airfoils: - - SNL 0015/47 SNL 0018/50 SNL 0021/50 - X (Y X (Y X (Y -0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 -0.00020 0.00166 0.00337 0.00646 0.00343 0.00790 -0.00508 0.01091 0.01274 0.01431 0.01291 0.01728 -0.01507 0.02060 0.02713 0.02282 0.02740 0.02735 -0.02872 0.02867 0.04621 0.03160 0.04653 0.03771 -0.04729 0.03615 0.06970 0.04042 0.07001 0.04806 -0.07062 0.04329 0.09730 0.04903 0.09753 0.05814 -0.09832 0.05006 0.12870 0.05726 0.12878 0.06772 -0.13002 0.05630 0.16353 0.06491 0.16339 0.07660 -0.16533 0.06192 0.20142 0.07183 0.20098 0.08460 -0.20386 0.06678 0.24193 0.07786 0.24113 0.09152 -0.24517 0.07080 0.28464 0.08283 0.28339 0.09721 -0.28880 0.07383 0.32907 0.08663 0.32730 0.10149 -0.33426 0.07575 0.37471 0.08908 0.37235 0.10417 -0.38104 0.07643 0.42107 0.09000 0.41805 0.10507 -0.42860 0.07556 0.46759 0.08902 0.46384 0.10379 -0.47688 0.07272 0.51422 0.08561 0.50965 0.09968 -0.52610 0.06808 0.56140 0.07982 0.55603 0.09272 -0.57603 0.06216 0.60914 0.07234 0.60311 0.08368 -0.62618 0.05535 0.65698 0.06379 0.65048 0.07323 -0.67600 0.04801 0.70440 0.05462 0.69767 0.06193 -0.72489 0.04046 0.75083 0.04535 0.74412 0.05037 -0.77244 0.03306 0.79560 0.03642 0.78921 0.03911 -0.81734 0.02608 0.83798 0.02827 0.83220 0.02869 -0.85951 0.01979 0.87718 0.02125 0.87224 0.01959 -0.89801 0.01441 0.91233 0.01562 0.90843 0.01217 -0.93212 0.01005 0.94258 0.01150 0.93980 0.00663 -0.96114 0.00676 0.96711 0.00881 0.96541 0.00296 -0.98447 0.00448 0.98519 0.00740 0.98439 0.00095 -0.99685 0.00349 0.99627 0.00687 0.99606 0.00015 -1.00000 0.00000 1.00000 0.00678 1.00000 0.00000 - -The 18/50 was thickened up near the trailing edge so we could actually build it (we can't make a razor-edged extrusion). Although we had to do a similar thing with the other two airfoils when we built models, I don't have those coordinates available. diff --git a/examples/SNL17m/airfoils/NACA_0018.txt b/examples/SNL17m/airfoils/NACA_0018.txt deleted file mode 100644 index 39bdb98e..00000000 --- a/examples/SNL17m/airfoils/NACA_0018.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.277853 0 -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 7.40293088030186e-03 - 9.89671379974747e-01 5.52312701646428e-03 - 9.64477131182153e-01 2.48535959199292e-03 - 9.39158624174899e-01 1.50473515887706e-03 - 9.13813162279310e-01 2.76632310473288e-03 - 8.88553591831403e-01 2.67289317456605e-03 - 8.63480304357990e-01 1.25212903431862e-03 - 8.38670008821752e-01 -1.30558063733301e-03 - 8.14184038980280e-01 -4.88132537219822e-03 - 7.90073507481042e-01 -9.41733442728799e-03 - 7.66396243180071e-01 -1.48824286806251e-02 - 7.43171762127060e-01 -2.11375614462018e-02 - 7.20393063763985e-01 -2.79720058036821e-02 - 6.98115514389012e-01 -3.52505652104797e-02 - 6.76338951051125e-01 -4.28545172802418e-02 - 6.54963698148296e-01 -5.06468535065558e-02 - 6.33966484340103e-01 -5.84975164629663e-02 - 6.13322712460925e-01 -6.62930528103014e-02 - 5.93009124541476e-01 -7.39276794968806e-02 - 5.73007900047194e-01 -8.13122377370243e-02 - 5.53307401144792e-01 -8.83796608479274e-02 - 5.33898576587071e-01 -9.50621639631644e-02 - 5.14779223154629e-01 -1.01312996030444e-01 - 4.95954396665602e-01 -1.07104315450230e-01 - 4.77430350386696e-01 -1.12408644224066e-01 - 4.59214886856257e-01 -1.17204581007605e-01 - 4.41321190252217e-01 -1.21492098858552e-01 - 4.23765543793179e-01 -1.25284369716559e-01 - 4.06561760993008e-01 -1.28585742506391e-01 - 3.89721882904375e-01 -1.31398677720742e-01 - 3.73261236217240e-01 -1.33753884336962e-01 - 3.57188855965126e-01 -1.35648590203785e-01 - 3.41516689450044e-01 -1.37114853045608e-01 - 3.26253343070801e-01 -1.38165142239116e-01 - 3.11407100100747e-01 -1.38843026632002e-01 - 2.96983147380361e-01 -1.39134253049587e-01 - 2.82986150094719e-01 -1.39079401993577e-01 - 2.69419666676137e-01 -1.38717378594186e-01 - 2.56284310763483e-01 -1.38047377841284e-01 - 2.43581181695766e-01 -1.37097182609024e-01 - 2.31309755891564e-01 -1.35878986181238e-01 - 2.19467527384275e-01 -1.34419669774399e-01 - 2.08052199943945e-01 -1.32734565881183e-01 - 1.97060878905940e-01 -1.30836024341106e-01 - 1.86487605109370e-01 -1.28750195729576e-01 - 1.76328427331090e-01 -1.26489260780352e-01 - 1.66576425927345e-01 -1.24072846261382e-01 - 1.57224710042703e-01 -1.21517422330090e-01 - 1.48263768632238e-01 -1.18845748716941e-01 - 1.39686465720747e-01 -1.16068315902589e-01 - 1.31484076933721e-01 -1.13199808713479e-01 - 1.23644002494218e-01 -1.10264064411865e-01 - 1.16158389148626e-01 -1.07268856271171e-01 - 1.09017608460481e-01 -1.04225445806672e-01 - 1.02208845279057e-01 -1.01150464979009e-01 - 9.57204441656418e-02 -9.80567235916097e-02 - 8.95431256675966e-02 -9.49505777251444e-02 - 8.36654273586364e-02 -9.18425702625302e-02 - 7.80736545281131e-02 -8.87461053661387e-02 - 7.27609142941316e-02 -8.56618586963429e-02 - 6.77181375640349e-02 -8.25939725469746e-02 - 6.29314267915325e-02 -7.95542155266183e-02 - 5.83918736326263e-02 -7.65460757142504e-02 - 5.40924087603125e-02 -7.35696428637186e-02 - 5.00238126094804e-02 -7.06282944642002e-02 - 4.61744194566202e-02 -6.77294750039665e-02 - 4.25343792761530e-02 -6.48775856834624e-02 - 3.90962763038171e-02 -6.20732990855308e-02 - 3.58516054447007e-02 -5.93185385599462e-02 - 3.27924500315299e-02 -5.66146352875974e-02 - 2.99188717479619e-02 -5.39556602195701e-02 - 2.72190044082920e-02 -5.13479767861748e-02 - 2.46896838543740e-02 -4.87892184809108e-02 - 2.23254525385638e-02 -4.62783210206995e-02 - 2.01130198509196e-02 -4.38228788319503e-02 - 1.80527586585474e-02 -4.14178634132421e-02 - 1.61356703170338e-02 -3.90662785024268e-02 - 1.43526037214418e-02 -3.67706864368368e-02 - 1.26925112458821e-02 -3.45344165274944e-02 - 1.11706366374529e-02 -3.23446888414334e-02 - 9.77352700565712e-03 -3.02054531089257e-02 - 8.49040361517659e-03 -2.81209420953160e-02 - 7.31269112385052e-03 -2.60938026465363e-02 - 6.25433551768215e-03 -2.41164241729582e-02 - 5.30829698548717e-03 -2.21892077859789e-02 - 4.45476327462913e-03 -2.03207332985441e-02 - 3.64530110445795e-03 -1.85320357914752e-02 - 2.91174185051685e-03 -1.68006712086556e-02 - 2.31718348065112e-03 -1.51053653630030e-02 - 1.82941121798937e-03 -1.34554413874920e-02 - 1.42352546318114e-03 -1.18578324134269e-02 - 1.12283938796851e-03 -1.03129812659207e-02 - 8.95185703762229e-04 -8.82257444647604e-03 - 7.19623688087765e-04 -7.39115890366439e-03 - 5.77020939120505e-04 -6.01882030127991e-03 - 4.52369924559997e-04 -4.70522667482128e-03 - 3.33108736652917e-04 -3.44876744129361e-03 - 2.19678789799849e-04 -2.24707655933577e-03 - 1.10470627512087e-04 -1.09799301605679e-03 - 0.00000000000000e+00 0.00000000000000e+00 - 1.02143597426640e-04 1.10023219599336e-03 - 2.01309614692119e-04 7.4e-03 - 2.99835334696142e-04 7.4e-03 - 4.01625134276334e-04 7.4e-03 - 5.03744497735996e-04 7.4e-03 - 6.18346425662303e-04 7.4e-03 - 7.62162373651962e-04 7.4e-03 - 9.44028461513286e-04 7.4e-03 - 1.18336819581177e-03 7.4e-03 - 1.50884511188477e-03 7.4e-03 - 1.89788727592515e-03 7.4e-03 - 2.36899110997143e-03 7.4e-03 - 2.93906777320867e-03 7.4e-03 - 3.59867586435142e-03 7.4e-03 - 4.30670940618765e-03 7.4e-03 - 5.09720271325558e-03 7.4e-03 - 5.99752167084764e-03 7.4e-03 - 7.00809148016107e-03 7.4e-03 - 8.11991886289441e-03 7.4e-03 - 9.32294853441525e-03 7.4e-03 - 1.06452748433505e-02 7.4e-03 - 1.20919016758476e-02 7.4e-03 - 1.36657091050637e-02 7.4e-03 - 1.53619984984854e-02 7.4e-03 - 1.71997879098679e-02 7.4e-03 - 1.91847655820185e-02 7.4e-03 - 2.13253359844419e-02 7.4e-03 - 2.36315005758345e-02 7.4e-03 - 2.61083491713133e-02 7.4e-03 - 2.87612971194336e-02 7.4e-03 - 3.15981507017924e-02 7.4e-03 - 3.46280735398022e-02 7.4e-03 - 3.78535969542887e-02 7.4e-03 - 4.12850297637147e-02 7.4e-03 - 4.49307842744234e-02 7.4e-03 - 4.87981987096494e-02 7.4e-03 - 5.28961002593181e-02 7.4e-03 - 5.72308802904099e-02 7.4e-03 - 6.18143169001669e-02 7.4e-03 - 6.66558158361478e-02 7.4e-03 - 7.17628435388181e-02 7.4e-03 - 7.71433685208692e-02 7.4e-03 - 8.28066597109082e-02 7.4e-03 - 8.87623370313537e-02 7.4e-03 - 9.50225498149768e-02 7.4e-03 - 1.01593365906552e-01 7.4e-03 - 1.08484689743345e-01 7.4e-03 - 1.15707532058366e-01 7.4e-03 - 1.23267869284954e-01 7.4e-03 - 1.31175086465833e-01 7.4e-03 - 1.39439557403268e-01 7.4e-03 - 1.48067257045342e-01 7.4e-03 - 1.57063639519303e-01 7.4e-03 - 1.66438358327925e-01 7.4e-03 - 1.76196693213626e-01 7.4e-03 - 1.86343854246133e-01 7.4e-03 - 1.96885647258938e-01 7.4e-03 - 2.07825319991041e-01 7.4e-03 - 2.19166830204027e-01 7.4e-03 - 2.30911494004837e-01 7.4e-03 - 2.43061659957463e-01 7.4e-03 - 2.55619522433114e-01 7.4e-03 - 2.68586808602858e-01 7.4e-03 - 2.81964767633922e-01 7.4e-03 - 2.95753029530419e-01 7.4e-03 - 3.09951274377490e-01 7.4e-03 - 3.24559071166843e-01 7.4e-03 - 3.39576055104730e-01 7.4e-03 - 3.55000214209568e-01 7.4e-03 - 3.70830022781953e-01 7.4e-03 - 3.87063242925100e-01 7.4e-03 - 4.03697484944282e-01 7.4e-03 - 4.20727347071592e-01 7.4e-03 - 4.38151752431921e-01 7.4e-03 - 4.55964245711291e-01 7.4e-03 - 4.74161067405196e-01 7.4e-03 - 4.92733472564726e-01 7.4e-03 - 5.11676517362321e-01 7.4e-03 - 5.30985351170107e-01 7.4e-03 - 5.50653338799897e-01 7.4e-03 - 5.70668704030238e-01 7.4e-03 - 5.91022299396154e-01 7.4e-03 - 6.11704971014609e-01 7.4e-03 - 6.32703405878887e-01 7.4e-03 - 6.54007799159681e-01 7.4e-03 - 6.75603313526683e-01 7.4e-03 - 6.97479344035197e-01 7.4e-03 - 7.19619100665882e-01 7.4e-03 - 7.42007863814197e-01 7.4e-03 - 7.64633916307294e-01 7.4e-03 - 7.87480347506928e-01 7.4e-03 - 8.10530974553361e-01 7.4e-03 - 8.33766686857151e-01 7.4e-03 - 8.57171368568559e-01 7.4e-03 - 8.80727606307419e-01 7.4e-03 - 9.04416064906437e-01 7.4e-03 - 9.28217017828997e-01 7.4e-03 - 9.52108466170963e-01 7.4e-03 - 9.76048832000119e-01 7.4e-03 - 1.00000000000000e+00 7.4e-03 diff --git a/examples/SNL17m/airfoils/NACA_0018_Coords.txt b/examples/SNL17m/airfoils/NACA_0018_Coords.txt deleted file mode 100644 index 39bdb98e..00000000 --- a/examples/SNL17m/airfoils/NACA_0018_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.277853 0 -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 7.40293088030186e-03 - 9.89671379974747e-01 5.52312701646428e-03 - 9.64477131182153e-01 2.48535959199292e-03 - 9.39158624174899e-01 1.50473515887706e-03 - 9.13813162279310e-01 2.76632310473288e-03 - 8.88553591831403e-01 2.67289317456605e-03 - 8.63480304357990e-01 1.25212903431862e-03 - 8.38670008821752e-01 -1.30558063733301e-03 - 8.14184038980280e-01 -4.88132537219822e-03 - 7.90073507481042e-01 -9.41733442728799e-03 - 7.66396243180071e-01 -1.48824286806251e-02 - 7.43171762127060e-01 -2.11375614462018e-02 - 7.20393063763985e-01 -2.79720058036821e-02 - 6.98115514389012e-01 -3.52505652104797e-02 - 6.76338951051125e-01 -4.28545172802418e-02 - 6.54963698148296e-01 -5.06468535065558e-02 - 6.33966484340103e-01 -5.84975164629663e-02 - 6.13322712460925e-01 -6.62930528103014e-02 - 5.93009124541476e-01 -7.39276794968806e-02 - 5.73007900047194e-01 -8.13122377370243e-02 - 5.53307401144792e-01 -8.83796608479274e-02 - 5.33898576587071e-01 -9.50621639631644e-02 - 5.14779223154629e-01 -1.01312996030444e-01 - 4.95954396665602e-01 -1.07104315450230e-01 - 4.77430350386696e-01 -1.12408644224066e-01 - 4.59214886856257e-01 -1.17204581007605e-01 - 4.41321190252217e-01 -1.21492098858552e-01 - 4.23765543793179e-01 -1.25284369716559e-01 - 4.06561760993008e-01 -1.28585742506391e-01 - 3.89721882904375e-01 -1.31398677720742e-01 - 3.73261236217240e-01 -1.33753884336962e-01 - 3.57188855965126e-01 -1.35648590203785e-01 - 3.41516689450044e-01 -1.37114853045608e-01 - 3.26253343070801e-01 -1.38165142239116e-01 - 3.11407100100747e-01 -1.38843026632002e-01 - 2.96983147380361e-01 -1.39134253049587e-01 - 2.82986150094719e-01 -1.39079401993577e-01 - 2.69419666676137e-01 -1.38717378594186e-01 - 2.56284310763483e-01 -1.38047377841284e-01 - 2.43581181695766e-01 -1.37097182609024e-01 - 2.31309755891564e-01 -1.35878986181238e-01 - 2.19467527384275e-01 -1.34419669774399e-01 - 2.08052199943945e-01 -1.32734565881183e-01 - 1.97060878905940e-01 -1.30836024341106e-01 - 1.86487605109370e-01 -1.28750195729576e-01 - 1.76328427331090e-01 -1.26489260780352e-01 - 1.66576425927345e-01 -1.24072846261382e-01 - 1.57224710042703e-01 -1.21517422330090e-01 - 1.48263768632238e-01 -1.18845748716941e-01 - 1.39686465720747e-01 -1.16068315902589e-01 - 1.31484076933721e-01 -1.13199808713479e-01 - 1.23644002494218e-01 -1.10264064411865e-01 - 1.16158389148626e-01 -1.07268856271171e-01 - 1.09017608460481e-01 -1.04225445806672e-01 - 1.02208845279057e-01 -1.01150464979009e-01 - 9.57204441656418e-02 -9.80567235916097e-02 - 8.95431256675966e-02 -9.49505777251444e-02 - 8.36654273586364e-02 -9.18425702625302e-02 - 7.80736545281131e-02 -8.87461053661387e-02 - 7.27609142941316e-02 -8.56618586963429e-02 - 6.77181375640349e-02 -8.25939725469746e-02 - 6.29314267915325e-02 -7.95542155266183e-02 - 5.83918736326263e-02 -7.65460757142504e-02 - 5.40924087603125e-02 -7.35696428637186e-02 - 5.00238126094804e-02 -7.06282944642002e-02 - 4.61744194566202e-02 -6.77294750039665e-02 - 4.25343792761530e-02 -6.48775856834624e-02 - 3.90962763038171e-02 -6.20732990855308e-02 - 3.58516054447007e-02 -5.93185385599462e-02 - 3.27924500315299e-02 -5.66146352875974e-02 - 2.99188717479619e-02 -5.39556602195701e-02 - 2.72190044082920e-02 -5.13479767861748e-02 - 2.46896838543740e-02 -4.87892184809108e-02 - 2.23254525385638e-02 -4.62783210206995e-02 - 2.01130198509196e-02 -4.38228788319503e-02 - 1.80527586585474e-02 -4.14178634132421e-02 - 1.61356703170338e-02 -3.90662785024268e-02 - 1.43526037214418e-02 -3.67706864368368e-02 - 1.26925112458821e-02 -3.45344165274944e-02 - 1.11706366374529e-02 -3.23446888414334e-02 - 9.77352700565712e-03 -3.02054531089257e-02 - 8.49040361517659e-03 -2.81209420953160e-02 - 7.31269112385052e-03 -2.60938026465363e-02 - 6.25433551768215e-03 -2.41164241729582e-02 - 5.30829698548717e-03 -2.21892077859789e-02 - 4.45476327462913e-03 -2.03207332985441e-02 - 3.64530110445795e-03 -1.85320357914752e-02 - 2.91174185051685e-03 -1.68006712086556e-02 - 2.31718348065112e-03 -1.51053653630030e-02 - 1.82941121798937e-03 -1.34554413874920e-02 - 1.42352546318114e-03 -1.18578324134269e-02 - 1.12283938796851e-03 -1.03129812659207e-02 - 8.95185703762229e-04 -8.82257444647604e-03 - 7.19623688087765e-04 -7.39115890366439e-03 - 5.77020939120505e-04 -6.01882030127991e-03 - 4.52369924559997e-04 -4.70522667482128e-03 - 3.33108736652917e-04 -3.44876744129361e-03 - 2.19678789799849e-04 -2.24707655933577e-03 - 1.10470627512087e-04 -1.09799301605679e-03 - 0.00000000000000e+00 0.00000000000000e+00 - 1.02143597426640e-04 1.10023219599336e-03 - 2.01309614692119e-04 7.4e-03 - 2.99835334696142e-04 7.4e-03 - 4.01625134276334e-04 7.4e-03 - 5.03744497735996e-04 7.4e-03 - 6.18346425662303e-04 7.4e-03 - 7.62162373651962e-04 7.4e-03 - 9.44028461513286e-04 7.4e-03 - 1.18336819581177e-03 7.4e-03 - 1.50884511188477e-03 7.4e-03 - 1.89788727592515e-03 7.4e-03 - 2.36899110997143e-03 7.4e-03 - 2.93906777320867e-03 7.4e-03 - 3.59867586435142e-03 7.4e-03 - 4.30670940618765e-03 7.4e-03 - 5.09720271325558e-03 7.4e-03 - 5.99752167084764e-03 7.4e-03 - 7.00809148016107e-03 7.4e-03 - 8.11991886289441e-03 7.4e-03 - 9.32294853441525e-03 7.4e-03 - 1.06452748433505e-02 7.4e-03 - 1.20919016758476e-02 7.4e-03 - 1.36657091050637e-02 7.4e-03 - 1.53619984984854e-02 7.4e-03 - 1.71997879098679e-02 7.4e-03 - 1.91847655820185e-02 7.4e-03 - 2.13253359844419e-02 7.4e-03 - 2.36315005758345e-02 7.4e-03 - 2.61083491713133e-02 7.4e-03 - 2.87612971194336e-02 7.4e-03 - 3.15981507017924e-02 7.4e-03 - 3.46280735398022e-02 7.4e-03 - 3.78535969542887e-02 7.4e-03 - 4.12850297637147e-02 7.4e-03 - 4.49307842744234e-02 7.4e-03 - 4.87981987096494e-02 7.4e-03 - 5.28961002593181e-02 7.4e-03 - 5.72308802904099e-02 7.4e-03 - 6.18143169001669e-02 7.4e-03 - 6.66558158361478e-02 7.4e-03 - 7.17628435388181e-02 7.4e-03 - 7.71433685208692e-02 7.4e-03 - 8.28066597109082e-02 7.4e-03 - 8.87623370313537e-02 7.4e-03 - 9.50225498149768e-02 7.4e-03 - 1.01593365906552e-01 7.4e-03 - 1.08484689743345e-01 7.4e-03 - 1.15707532058366e-01 7.4e-03 - 1.23267869284954e-01 7.4e-03 - 1.31175086465833e-01 7.4e-03 - 1.39439557403268e-01 7.4e-03 - 1.48067257045342e-01 7.4e-03 - 1.57063639519303e-01 7.4e-03 - 1.66438358327925e-01 7.4e-03 - 1.76196693213626e-01 7.4e-03 - 1.86343854246133e-01 7.4e-03 - 1.96885647258938e-01 7.4e-03 - 2.07825319991041e-01 7.4e-03 - 2.19166830204027e-01 7.4e-03 - 2.30911494004837e-01 7.4e-03 - 2.43061659957463e-01 7.4e-03 - 2.55619522433114e-01 7.4e-03 - 2.68586808602858e-01 7.4e-03 - 2.81964767633922e-01 7.4e-03 - 2.95753029530419e-01 7.4e-03 - 3.09951274377490e-01 7.4e-03 - 3.24559071166843e-01 7.4e-03 - 3.39576055104730e-01 7.4e-03 - 3.55000214209568e-01 7.4e-03 - 3.70830022781953e-01 7.4e-03 - 3.87063242925100e-01 7.4e-03 - 4.03697484944282e-01 7.4e-03 - 4.20727347071592e-01 7.4e-03 - 4.38151752431921e-01 7.4e-03 - 4.55964245711291e-01 7.4e-03 - 4.74161067405196e-01 7.4e-03 - 4.92733472564726e-01 7.4e-03 - 5.11676517362321e-01 7.4e-03 - 5.30985351170107e-01 7.4e-03 - 5.50653338799897e-01 7.4e-03 - 5.70668704030238e-01 7.4e-03 - 5.91022299396154e-01 7.4e-03 - 6.11704971014609e-01 7.4e-03 - 6.32703405878887e-01 7.4e-03 - 6.54007799159681e-01 7.4e-03 - 6.75603313526683e-01 7.4e-03 - 6.97479344035197e-01 7.4e-03 - 7.19619100665882e-01 7.4e-03 - 7.42007863814197e-01 7.4e-03 - 7.64633916307294e-01 7.4e-03 - 7.87480347506928e-01 7.4e-03 - 8.10530974553361e-01 7.4e-03 - 8.33766686857151e-01 7.4e-03 - 8.57171368568559e-01 7.4e-03 - 8.80727606307419e-01 7.4e-03 - 9.04416064906437e-01 7.4e-03 - 9.28217017828997e-01 7.4e-03 - 9.52108466170963e-01 7.4e-03 - 9.76048832000119e-01 7.4e-03 - 1.00000000000000e+00 7.4e-03 diff --git a/examples/SNL17m/airfoils/NACA_0021.csv b/examples/SNL17m/airfoils/NACA_0021.csv new file mode 100644 index 00000000..7079c688 --- /dev/null +++ b/examples/SNL17m/airfoils/NACA_0021.csv @@ -0,0 +1,37 @@ +100.0001,0 +100,0.221 +95,1.412 +90,2.534 +80,4.591 +70,6.412 +60,7.986 +50,9.265 +40,10.156 +30,10.504 +25,10.397 +20,10.04 +15,9.354 +10,8.195 +7.5,7.35 +5,6.221 +2.5,4.576 +1.25,3.315 +0,0 +1.25,-3.315 +2.5,-4.576 +5,-6.221 +7.5,-7.35 +10,-8.195 +15,-9.354 +20,-10.04 +25,-10.397 +30,-10.504 +40,-10.156 +50,-9.265 +60,-7.986 +70,-6.412 +80,-4.591 +90,-2.534 +95,-1.412 +100,-0.221 +100.0001,0 \ No newline at end of file diff --git a/examples/SNL17m/airfoils/NACA_0021.dat b/examples/SNL17m/airfoils/NACA_0021.dat new file mode 100644 index 00000000..086fb2f0 --- /dev/null +++ b/examples/SNL17m/airfoils/NACA_0021.dat @@ -0,0 +1,1211 @@ +Title: NACA0021 +Thickness to Chord Ratio: 0.21 +Zero Lift AOA (deg): 0.0 +Reverse Camber Direction: 0 + +Reynolds Number: 1e4 +BV Dyn. Stall Model - Positive Stall AOA (deg): 1.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -1.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 5.73 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1 +AOA (deg) CL CD Cm25 +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -0.453900000000000 0.405000000000000 0 +-22 -0.300200000000000 0.329000000000000 0 +-20 -0.200600000000000 0.282000000000000 0 +-18 -0.103500000000000 0.238000000000000 0 +-16 -0.0123000000000000 0.196000000000000 0 +-14 0.0658000000000000 0.158000000000000 0 +-12 0.127600000000000 0.123000000000000 0 +-10 0.158100000000000 0.0750000000000000 0 +-9 0.158100000000000 0.0575000000000000 0 +-8 0.147500000000000 0.0538000000000000 0 +-7 0.140000000000000 0.0507000000000000 0 +-6 0.124000000000000 0.0480000000000000 0 +-5 0.115600000000000 0.0459000000000000 0 +-4 0.0995000000000000 0.0441000000000000 0 +-3 0.0854000000000000 0.0429000000000000 0 +-2 0.0631000000000000 0.0420000000000000 0 +-1 0.0320000000000000 0.0414000000000000 0 +0 0 0.0413000000000000 0 +1 -0.0320000000000000 0.0414000000000000 0 +2 -0.0631000000000000 0.0420000000000000 0 +3 -0.0854000000000000 0.0429000000000000 0 +4 -0.0995000000000000 0.0441000000000000 0 +5 -0.115600000000000 0.0459000000000000 0 +6 -0.124000000000000 0.0480000000000000 0 +7 -0.140000000000000 0.0507000000000000 0 +8 -0.147500000000000 0.0538000000000000 0 +9 -0.158100000000000 0.0575000000000000 0 +10 -0.158100000000000 0.0750000000000000 0 +12 -0.127600000000000 0.123000000000000 0 +14 -0.0658000000000000 0.158000000000000 0 +16 0.0123000000000000 0.196000000000000 0 +18 0.103500000000000 0.238000000000000 0 +20 0.200600000000000 0.282000000000000 0 +22 0.300200000000000 0.329000000000000 0 +25 0.453900000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 + +Reynolds Number: 2e4 +BV Dyn. Stall Model - Positive Stall AOA (deg): 1.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -1.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 5.73 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1 +AOA (deg) CL CD Cm25 +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -0.461800000000000 0.405000000000000 0 +-22 -0.310300000000000 0.329000000000000 0 +-20 -0.212400000000000 0.282000000000000 0 +-18 -0.118000000000000 0.238000000000000 0 +-16 -0.0331000000000000 0.196000000000000 0 +-14 0.0362000000000000 0.158000000000000 0 +-12 0.0713000000000000 0.123000000000000 0 +-10 0.0506000000000000 0.0700000000000000 0 +-9 0.0190000000000000 0.0435000000000000 0 +-8 -0.0120000000000000 0.0407000000000000 0 +-7 -0.0266000000000000 0.0382000000000000 0 +-6 -0.0475000000000000 0.0362000000000000 0 +-5 -0.0505000000000000 0.0345000000000000 0 +-4 -0.0619000000000000 0.0332000000000000 0 +-3 -0.0472000000000000 0.0321000000000000 0 +-2 -0.0393000000000000 0.0314000000000000 0 +-1 -0.0243000000000000 0.0310000000000000 0 +0 0 0.0309000000000000 0 +1 0.0243000000000000 0.0310000000000000 0 +2 0.0393000000000000 0.0314000000000000 0 +3 0.0472000000000000 0.0321000000000000 0 +4 0.0619000000000000 0.0332000000000000 0 +5 0.0505000000000000 0.0345000000000000 0 +6 0.0475000000000000 0.0362000000000000 0 +7 0.0266000000000000 0.0382000000000000 0 +8 0.0120000000000000 0.0407000000000000 0 +9 -0.0190000000000000 0.0435000000000000 0 +10 -0.0506000000000000 0.0700000000000000 0 +12 -0.0713000000000000 0.123000000000000 0 +14 -0.0362000000000000 0.158000000000000 0 +16 0.0331000000000000 0.196000000000000 0 +18 0.118000000000000 0.238000000000000 0 +20 0.212400000000000 0.282000000000000 0 +22 0.310300000000000 0.329000000000000 0 +25 0.461800000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 + +Reynolds Number: 4e4 +BV Dyn. Stall Model - Positive Stall AOA (deg): 3.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -3.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 4.309 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 0.526 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -0.526 +AOA (deg) CL CD Cm25 +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -0.480200000000000 0.405000000000000 0 +-22 -0.334500000000000 0.329000000000000 0 +-20 -0.241400000000000 0.282000000000000 0 +-18 -0.161900000000000 0.238000000000000 0 +-16 -0.0981000000000000 0.196000000000000 0 +-14 -0.0833000000000000 0.158000000000000 0 +-12 -0.166000000000000 0.123000000000000 0 +-10 -0.269100000000000 0.0620000000000000 0 +-9 -0.316200000000000 0.0343000000000000 0 +-8 -0.342000000000000 0.0319000000000000 0 +-7 -0.342700000000000 0.0297000000000000 0 +-6 -0.338200000000000 0.0279000000000000 0 +-5 -0.308600000000000 0.0264000000000000 0 +-4 -0.273000000000000 0.0253000000000000 0 +-3 -0.210300000000000 0.0243000000000000 0 +-2 -0.146500000000000 0.0237000000000000 0 +-1 -0.0752000000000000 0.0233000000000000 0 +0 0 0.0232000000000000 0 +1 0.0752000000000000 0.0233000000000000 0 +2 0.146500000000000 0.0237000000000000 0 +3 0.210300000000000 0.0243000000000000 0 +4 0.273000000000000 0.0253000000000000 0 +5 0.308600000000000 0.0264000000000000 0 +6 0.338200000000000 0.0279000000000000 0 +7 0.342700000000000 0.0297000000000000 0 +8 0.342000000000000 0.0319000000000000 0 +9 0.316200000000000 0.0343000000000000 0 +10 0.269100000000000 0.0620000000000000 0 +12 0.166000000000000 0.123000000000000 0 +14 0.0833000000000000 0.158000000000000 0 +16 0.0981000000000000 0.196000000000000 0 +18 0.161900000000000 0.238000000000000 0 +20 0.241400000000000 0.282000000000000 0 +22 0.334500000000000 0.329000000000000 0 +25 0.480200000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 + +Reynolds Number: 8e4 +BV Dyn. Stall Model - Positive Stall AOA (deg): 4.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -4.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 5.277 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 0.829 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -0.829 +AOA (deg) CL CD Cm25 +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -0.529700000000000 0.405000000000000 0 +-22 -0.409100000000000 0.329000000000000 0 +-20 -0.347500000000000 0.282000000000000 0 +-18 -0.322100000000000 0.238000000000000 0 +-16 -0.349900000000000 0.196000000000000 0 +-14 -0.429600000000000 0.158000000000000 0 +-12 -0.522800000000000 0.123000000000000 0 +-11 -0.556400000000000 0.0700000000000000 0 +-10 -0.578000000000000 0.0297000000000000 0 +-9 -0.587400000000000 0.0273000000000000 0 +-8 -0.575100000000000 0.0252000000000000 0 +-7 -0.544500000000000 0.0233000000000000 0 +-6 -0.495300000000000 0.0217000000000000 0 +-5 -0.432400000000000 0.0204000000000000 0 +-4 -0.356400000000000 0.0194000000000000 0 +-3 -0.273100000000000 0.0186000000000000 0 +-2 -0.183900000000000 0.0181000000000000 0 +-1 -0.0921000000000000 0.0178000000000000 0 +0 0 0.0177000000000000 0 +1 0.0921000000000000 0.0178000000000000 0 +2 0.183900000000000 0.0181000000000000 0 +3 0.273100000000000 0.0186000000000000 0 +4 0.356400000000000 0.0194000000000000 0 +5 0.432400000000000 0.0204000000000000 0 +6 0.495300000000000 0.0217000000000000 0 +7 0.544500000000000 0.0233000000000000 0 +8 0.575100000000000 0.0252000000000000 0 +9 0.587400000000000 0.0273000000000000 0 +10 0.578000000000000 0.0297000000000000 0 +11 0.556400000000000 0.0700000000000000 0 +12 0.522800000000000 0.123000000000000 0 +14 0.429600000000000 0.158000000000000 0 +16 0.349900000000000 0.196000000000000 0 +18 0.322100000000000 0.238000000000000 0 +20 0.347500000000000 0.282000000000000 0 +22 0.409100000000000 0.329000000000000 0 +25 0.529700000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 + +Reynolds Number: 1.6e5 +BV Dyn. Stall Model - Positive Stall AOA (deg): 5.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -5.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 5.371 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.031 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.031 +AOA (deg) CL CD Cm25 +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -0.666400000000000 0.405000000000000 0 +-22 -0.602300000000000 0.329000000000000 0 +-20 -0.592000000000000 0.282000000000000 0 +-18 -0.609800000000000 0.238000000000000 0 +-16 -0.648700000000000 0.196000000000000 0 +-14 -0.699300000000000 0.158000000000000 0 +-13 -0.725500000000000 0.0860000000000000 0 +-12 -0.736300000000000 0.0292000000000000 0 +-11 -0.744300000000000 0.0266000000000000 0 +-10 -0.737400000000000 0.0243000000000000 0 +-9 -0.714800000000000 0.0222000000000000 0 +-8 -0.674500000000000 0.0204000000000000 0 +-7 -0.620900000000000 0.0187000000000000 0 +-6 -0.548600000000000 0.0174000000000000 0 +-5 -0.468700000000000 0.0163000000000000 0 +-4 -0.380000000000000 0.0155000000000000 0 +-3 -0.286100000000000 0.0148000000000000 0 +-2 -0.187900000000000 0.0143000000000000 0 +-1 -0.0842000000000000 0.0140000000000000 0 +0 0 0.0139000000000000 0 +1 0.0842000000000000 0.0140000000000000 0 +2 0.187900000000000 0.0143000000000000 0 +3 0.286100000000000 0.0148000000000000 0 +4 0.380000000000000 0.0155000000000000 0 +5 0.468700000000000 0.0163000000000000 0 +6 0.548600000000000 0.0174000000000000 0 +7 0.620900000000000 0.0187000000000000 0 +8 0.674500000000000 0.0204000000000000 0 +9 0.714800000000000 0.0222000000000000 0 +10 0.737400000000000 0.0243000000000000 0 +11 0.744300000000000 0.0266000000000000 0 +12 0.736300000000000 0.0292000000000000 0 +13 0.725500000000000 0.0860000000000000 0 +14 0.699300000000000 0.158000000000000 0 +16 0.648700000000000 0.196000000000000 0 +18 0.609800000000000 0.238000000000000 0 +20 0.592000000000000 0.282000000000000 0 +22 0.602300000000000 0.329000000000000 0 +25 0.666400000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 + +Reynolds Number: 3.6e5 +BV Dyn. Stall Model - Positive Stall AOA (deg): 5.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -5.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.32 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.32 +AOA (deg) CL CD Cm25 +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -0.886600000000000 0.405000000000000 0 +-22 -0.845300000000000 0.329000000000000 0 +-20 -0.839700000000000 0.282000000000000 0 +-18 -0.848900000000000 0.238000000000000 0 +-16 -0.871700000000000 0.196000000000000 0 +-15 -0.884000000000000 0.104000000000000 0 +-14 -0.893700000000000 0.0286000000000000 0 +-13 -0.897300000000000 0.0260000000000000 0 +-12 -0.893800000000000 0.0237000000000000 0 +-11 -0.877900000000000 0.0215000000000000 0 +-10 -0.850000000000000 0.0195000000000000 0 +-9 -0.802600000000000 0.0178000000000000 0 +-8 -0.743400000000000 0.0163000000000000 0 +-7 -0.672800000000000 0.0149000000000000 0 +-6 -0.589100000000000 0.0138000000000000 0 +-5 -0.499800000000000 0.0129000000000000 0 +-4 -0.404400000000000 0.0122000000000000 0 +-3 -0.302400000000000 0.0117000000000000 0 +-2 -0.220000000000000 0.0113000000000000 0 +-1 -0.110000000000000 0.0111000000000000 0 +0 0 0.0111000000000000 0 +1 0.110000000000000 0.0111000000000000 0 +2 0.220000000000000 0.0113000000000000 0 +3 0.302400000000000 0.0117000000000000 0 +4 0.404400000000000 0.0122000000000000 0 +5 0.499800000000000 0.0129000000000000 0 +6 0.589100000000000 0.0138000000000000 0 +7 0.672800000000000 0.0149000000000000 0 +8 0.743400000000000 0.0163000000000000 0 +9 0.802600000000000 0.0178000000000000 0 +10 0.850000000000000 0.0195000000000000 0 +11 0.877900000000000 0.0215000000000000 0 +12 0.893800000000000 0.0237000000000000 0 +13 0.897300000000000 0.0260000000000000 0 +14 0.893700000000000 0.0286000000000000 0 +15 0.884000000000000 0.104000000000000 0 +16 0.871700000000000 0.196000000000000 0 +18 0.848900000000000 0.238000000000000 0 +20 0.839700000000000 0.282000000000000 0 +22 0.845300000000000 0.329000000000000 0 +25 0.886600000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 + +Reynolds Number: 7e5 +BV Dyn. Stall Model - Positive Stall AOA (deg): 6.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -6.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.54 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.54 +AOA (deg) CL CD Cm25 +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -1.03500000000000 0.405000000000000 0 +-22 -0.994000000000000 0.329000000000000 0 +-20 -0.985800000000000 0.282000000000000 0 +-18 -0.991100000000000 0.238000000000000 0 +-17 -0.997300000000000 0.125000000000000 0 +-16 -1.00560000000000 0.0295000000000000 0 +-15 -1.01060000000000 0.0269000000000000 0 +-14 -1.01220000000000 0.0244000000000000 0 +-13 -1.00200000000000 0.0223000000000000 0 +-12 -0.984300000000000 0.0202000000000000 0 +-11 -0.954300000000000 0.0184000000000000 0 +-10 -0.909100000000000 0.0166000000000000 0 +-9 -0.849800000000000 0.0152000000000000 0 +-8 -0.780200000000000 0.0138000000000000 0 +-7 -0.698800000000000 0.0126000000000000 0 +-6 -0.610000000000000 0.0117000000000000 0 +-5 -0.514600000000000 0.0109000000000000 0 +-4 -0.412800000000000 0.0103000000000000 0 +-3 -0.330000000000000 0.00980000000000000 0 +-2 -0.220000000000000 0.00960000000000000 0 +-1 -0.110000000000000 0.00940000000000000 0 +0 0 0.00940000000000000 0 +1 0.110000000000000 0.00940000000000000 0 +2 0.220000000000000 0.00960000000000000 0 +3 0.330000000000000 0.00980000000000000 0 +4 0.412800000000000 0.0103000000000000 0 +5 0.514600000000000 0.0109000000000000 0 +6 0.610000000000000 0.0117000000000000 0 +7 0.698800000000000 0.0126000000000000 0 +8 0.780200000000000 0.0138000000000000 0 +9 0.849800000000000 0.0152000000000000 0 +10 0.909100000000000 0.0166000000000000 0 +11 0.954300000000000 0.0184000000000000 0 +12 0.984300000000000 0.0202000000000000 0 +13 1.00200000000000 0.0223000000000000 0 +14 1.01220000000000 0.0244000000000000 0 +15 1.01060000000000 0.0269000000000000 0 +16 1.00560000000000 0.0295000000000000 0 +17 0.997300000000000 0.125000000000000 0 +18 0.991100000000000 0.238000000000000 0 +20 0.985800000000000 0.282000000000000 0 +22 0.994000000000000 0.329000000000000 0 +25 1.03500000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 + +Reynolds Number: 1e6 +BV Dyn. Stall Model - Positive Stall AOA (deg): 6.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -6.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.65 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.65 +AOA (deg) CL CD Cm25 +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -1.10180000000000 0.405000000000000 0 +-22 -1.06440000000000 0.329000000000000 0 +-20 -1.05540000000000 0.282000000000000 0 +-18 -1.05880000000000 0.135000000000000 0 +-17 -1.06410000000000 0.0300000000000000 0 +-16 -1.06900000000000 0.0273000000000000 0 +-15 -1.07090000000000 0.0248000000000000 0 +-14 -1.06570000000000 0.0226000000000000 0 +-13 -1.04920000000000 0.0206000000000000 0 +-12 -1.02570000000000 0.0187000000000000 0 +-11 -0.986200000000000 0.0170000000000000 0 +-10 -0.936400000000000 0.0154000000000000 0 +-9 -0.869400000000000 0.0140000000000000 0 +-8 -0.793900000000000 0.0128000000000000 0 +-7 -0.710200000000000 0.0117000000000000 0 +-6 -0.619100000000000 0.0108000000000000 0 +-5 -0.519200000000000 0.0101000000000000 0 +-4 -0.440000000000000 0.00960000000000000 0 +-3 -0.330000000000000 0.00920000000000000 0 +-2 -0.220000000000000 0.00900000000000000 0 +-1 -0.110000000000000 0.00890000000000000 0 +0 0 0.00890000000000000 0 +1 0.110000000000000 0.00890000000000000 0 +2 0.220000000000000 0.00900000000000000 0 +3 0.330000000000000 0.00920000000000000 0 +4 0.440000000000000 0.00960000000000000 0 +5 0.519200000000000 0.0101000000000000 0 +6 0.619100000000000 0.0108000000000000 0 +7 0.710200000000000 0.0117000000000000 0 +8 0.793900000000000 0.0128000000000000 0 +9 0.869400000000000 0.0140000000000000 0 +10 0.936400000000000 0.0154000000000000 0 +11 0.986200000000000 0.0170000000000000 0 +12 1.02570000000000 0.0187000000000000 0 +13 1.04920000000000 0.0206000000000000 0 +14 1.06570000000000 0.0226000000000000 0 +15 1.07090000000000 0.0248000000000000 0 +16 1.06900000000000 0.0273000000000000 0 +17 1.06410000000000 0.0300000000000000 0 +18 1.05880000000000 0.135000000000000 0 +20 1.05540000000000 0.282000000000000 0 +22 1.06440000000000 0.329000000000000 0 +25 1.10180000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 + +Reynolds Number: 2e6 +BV Dyn. Stall Model - Positive Stall AOA (deg): 6.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -6.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.65 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.65 +AOA (deg) CL CD Cm25 +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -1.22300000000000 0.405000000000000 0 +-22 -1.18930000000000 0.329000000000000 0 +-20 -1.18120000000000 0.282000000000000 0 +-19 -1.17970000000000 0.145000000000000 0 +-18 -1.18140000000000 0.0285000000000000 0 +-17 -1.18240000000000 0.0260000000000000 0 +-16 -1.18230000000000 0.0236000000000000 0 +-15 -1.17470000000000 0.0215000000000000 0 +-14 -1.15800000000000 0.0196000000000000 0 +-13 -1.13050000000000 0.0179000000000000 0 +-12 -1.09060000000000 0.0162000000000000 0 +-11 -1.03980000000000 0.0148000000000000 0 +-10 -0.973900000000000 0.0135000000000000 0 +-9 -0.898600000000000 0.0124000000000000 0 +-8 -0.814300000000000 0.0114000000000000 0 +-7 -0.725400000000000 0.0105000000000000 0 +-6 -0.626800000000000 0.00980000000000000 0 +-5 -0.550000000000000 0.00920000000000000 0 +-4 -0.440000000000000 0.00890000000000000 0 +-3 -0.330000000000000 0.00860000000000000 0 +-2 -0.220000000000000 0.00840000000000000 0 +-1 -0.110000000000000 0.00830000000000000 0 +0 0 0.00820000000000000 0 +1 0.110000000000000 0.00830000000000000 0 +2 0.220000000000000 0.00840000000000000 0 +3 0.330000000000000 0.00860000000000000 0 +4 0.440000000000000 0.00890000000000000 0 +5 0.550000000000000 0.00920000000000000 0 +6 0.626800000000000 0.00980000000000000 0 +7 0.725400000000000 0.0105000000000000 0 +8 0.814300000000000 0.0114000000000000 0 +9 0.898600000000000 0.0124000000000000 0 +10 0.973900000000000 0.0135000000000000 0 +11 1.03980000000000 0.0148000000000000 0 +12 1.09060000000000 0.0162000000000000 0 +13 1.13050000000000 0.0179000000000000 0 +14 1.15800000000000 0.0196000000000000 0 +15 1.17470000000000 0.0215000000000000 0 +16 1.18230000000000 0.0236000000000000 0 +17 1.18240000000000 0.0260000000000000 0 +18 1.18140000000000 0.0285000000000000 0 +19 1.17970000000000 0.145000000000000 0 +20 1.18120000000000 0.282000000000000 0 +22 1.18930000000000 0.329000000000000 0 +25 1.22300000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 + +Reynolds Number: 5e6 +BV Dyn. Stall Model - Positive Stall AOA (deg): 6.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -6.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.76 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.76 +AOA (deg) CL CD Cm25 +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -1.34760000000000 0.405000000000000 0 +-22 -1.31300000000000 0.329000000000000 0 +-20 -1.30540000000000 0.0293000000000000 0 +-19 -1.30660000000000 0.0268000000000000 0 +-18 -1.30310000000000 0.0245000000000000 0 +-17 -1.29770000000000 0.0224000000000000 0 +-16 -1.28600000000000 0.0205000000000000 0 +-15 -1.26800000000000 0.0186000000000000 0 +-14 -1.24100000000000 0.0170000000000000 0 +-13 -1.19790000000000 0.0156000000000000 0 +-12 -1.14530000000000 0.0143000000000000 0 +-11 -1.07870000000000 0.0132000000000000 0 +-10 -1.00490000000000 0.0121000000000000 0 +-9 -0.922200000000000 0.0112000000000000 0 +-8 -0.833400000000000 0.0104000000000000 0 +-7 -0.735400000000000 0.00970000000000000 0 +-6 -0.660000000000000 0.00910000000000000 0 +-5 -0.550000000000000 0.00860000000000000 0 +-4 -0.440000000000000 0.00830000000000000 0 +-3 -0.330000000000000 0.00810000000000000 0 +-2 -0.220000000000000 0.00790000000000000 0 +-1 -0.110000000000000 0.00780000000000000 0 +0 0 0.00780000000000000 0 +1 0.110000000000000 0.00780000000000000 0 +2 0.220000000000000 0.00790000000000000 0 +3 0.330000000000000 0.00810000000000000 0 +4 0.440000000000000 0.00830000000000000 0 +5 0.550000000000000 0.00860000000000000 0 +6 0.660000000000000 0.00910000000000000 0 +7 0.735400000000000 0.00970000000000000 0 +8 0.833400000000000 0.0104000000000000 0 +9 0.922200000000000 0.0112000000000000 0 +10 1.00490000000000 0.0121000000000000 0 +11 1.07870000000000 0.0132000000000000 0 +12 1.14530000000000 0.0143000000000000 0 +13 1.19790000000000 0.0156000000000000 0 +14 1.24100000000000 0.0170000000000000 0 +15 1.26800000000000 0.0186000000000000 0 +16 1.28600000000000 0.0205000000000000 0 +17 1.29770000000000 0.0224000000000000 0 +18 1.30310000000000 0.0245000000000000 0 +19 1.30660000000000 0.0268000000000000 0 +20 1.30540000000000 0.0293000000000000 0 +22 1.31300000000000 0.329000000000000 0 +25 1.34760000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 + +Reynolds Number: 8e6 +BV Dyn. Stall Model - Positive Stall AOA (deg): 10.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -10.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.131 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.82 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.82 +AOA (deg) CL CD Cm25 +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-22 -1.45100000000000 0.329000000000000 0 +-20 -1.43500000000000 0.282000000000000 0 +-18 -1.41500000000000 0.135000000000000 0 +-16 -1.37700000000000 0.0199000000000000 0 +-15 -1.34400000000000 0.0184000000000000 0 +-14 -1.30100000000000 0.0170000000000000 0 +-13 -1.24800000000000 0.0157000000000000 0 +-12 -1.18200000000000 0.0145000000000000 0 +-11 -1.10800000000000 0.0134000000000000 0 +-10 -1.02400000000000 0.0124000000000000 0 +-9 -0.935000000000000 0.0115000000000000 0 +-8 -0.841000000000000 0.0107000000000000 0 +-7 -0.744000000000000 0.00990000000000000 0 +-6 -0.639000000000000 0.00930000000000000 0 +-5 -0.533000000000000 0.00880000000000000 0 +-4 -0.426000000000000 0.00840000000000000 0 +-3 -0.320000000000000 0.00800000000000000 0 +-2 -0.213000000000000 0.00780000000000000 0 +-1 -0.107000000000000 0.00770000000000000 0 +0 0 0.00760000000000000 0 +1 0.107000000000000 0.00770000000000000 0 +2 0.213000000000000 0.00780000000000000 0 +3 0.320000000000000 0.00800000000000000 0 +4 0.426000000000000 0.00840000000000000 0 +5 0.533000000000000 0.00880000000000000 0 +6 0.639000000000000 0.00930000000000000 0 +7 0.744000000000000 0.00990000000000000 0 +8 0.841000000000000 0.0107000000000000 0 +9 0.935000000000000 0.0115000000000000 0 +10 1.02400000000000 0.0124000000000000 0 +11 1.10800000000000 0.0134000000000000 0 +12 1.18200000000000 0.0145000000000000 0 +13 1.24800000000000 0.0157000000000000 0 +14 1.30100000000000 0.0170000000000000 0 +15 1.34400000000000 0.0184000000000000 0 +16 1.37700000000000 0.0199000000000000 0 +18 1.41500000000000 0.135000000000000 0 +20 1.43500000000000 0.282000000000000 0 +22 1.45100000000000 0.329000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 diff --git a/examples/SNL17m/airfoils/circular.csv b/examples/SNL17m/airfoils/circular.csv new file mode 100644 index 00000000..c4b4b2b2 --- /dev/null +++ b/examples/SNL17m/airfoils/circular.csv @@ -0,0 +1,100 @@ +1,0 +0.999013364,-0.03139526 +0.996057351,-0.062666617 +0.991143625,-0.093690657 +0.984291581,-0.124344944 +0.975528258,-0.154508497 +0.964888243,-0.184062276 +0.952413526,-0.212889646 +0.93815334,-0.240876837 +0.922163963,-0.267913397 +0.904508497,-0.293892626 +0.885256621,-0.318711995 +0.864484314,-0.342273553 +0.842273553,-0.364484314 +0.818711995,-0.385256621 +0.793892626,-0.404508497 +0.767913397,-0.422163963 +0.740876837,-0.43815334 +0.712889646,-0.452413526 +0.684062276,-0.464888243 +0.654508497,-0.475528258 +0.624344944,-0.484291581 +0.593690657,-0.491143625 +0.562666617,-0.496057351 +0.53139526,-0.499013364 +0.5,-0.5 +0.46860474,-0.499013364 +0.437333383,-0.496057351 +0.406309343,-0.491143625 +0.375655056,-0.484291581 +0.345491503,-0.475528258 +0.315937724,-0.464888243 +0.287110354,-0.452413526 +0.259123163,-0.43815334 +0.232086603,-0.422163963 +0.206107374,-0.404508497 +0.181288005,-0.385256621 +0.157726447,-0.364484314 +0.135515686,-0.342273553 +0.114743379,-0.318711995 +0.095491503,-0.293892626 +0.077836037,-0.267913397 +0.06184666,-0.240876837 +0.047586474,-0.212889646 +0.035111757,-0.184062276 +0.024471742,-0.154508497 +0.015708419,-0.124344944 +0.008856375,-0.093690657 +0.003942649,-0.062666617 +0.000986636,-0.03139526 +0.0,0.0 +0.000986636,0.03139526 +0.003942649,0.062666617 +0.008856375,0.093690657 +0.015708419,0.124344944 +0.024471742,0.154508497 +0.035111757,0.184062276 +0.047586474,0.212889646 +0.06184666,0.240876837 +0.077836037,0.267913397 +0.095491503,0.293892626 +0.114743379,0.318711995 +0.135515686,0.342273553 +0.157726447,0.364484314 +0.181288005,0.385256621 +0.206107374,0.404508497 +0.232086603,0.422163963 +0.259123163,0.43815334 +0.287110354,0.452413526 +0.315937724,0.464888243 +0.345491503,0.475528258 +0.375655056,0.484291581 +0.406309343,0.491143625 +0.437333383,0.496057351 +0.46860474,0.499013364 +0.5,0.5 +0.53139526,0.499013364 +0.562666617,0.496057351 +0.593690657,0.491143625 +0.624344944,0.484291581 +0.654508497,0.475528258 +0.684062276,0.464888243 +0.712889646,0.452413526 +0.740876837,0.43815334 +0.767913397,0.422163963 +0.793892626,0.404508497 +0.818711995,0.385256621 +0.842273553,0.364484314 +0.864484314,0.342273553 +0.885256621,0.318711995 +0.904508497,0.293892626 +0.922163963,0.267913397 +0.93815334,0.240876837 +0.952413526,0.212889646 +0.964888243,0.184062276 +0.975528258,0.154508497 +0.984291581,0.124344944 +0.991143625,0.093690657 +0.996057351,0.062666617 +0.999013364,0.03139526 diff --git a/examples/SNL17m/data/NuMAD_34m_TowerGeom.csv b/examples/SNL17m/data/NuMAD_34m_TowerGeom.csv deleted file mode 100644 index 91a80bc2..00000000 --- a/examples/SNL17m/data/NuMAD_34m_TowerGeom.csv +++ /dev/null @@ -1,54 +0,0 @@ -SNL_34m_Glass_BPE,,,,# Shear webs ->,0,# of stacks ->,2,Stack ID ->,1,2,Segment ID ->,1,10,DP Types,1,2,1,2,,,,,,,,,,,,,,,,,,,, -,,,,,,# of segments ->,2,Material ID ->,8,8,,,,,,,first entry in the CSV list is the exterior blade surface stack,,,,,,,,,,,,,,,,,,,,, -Sta.#,Blade span (m),Airfoil Shape File,TE Type,Twist (deg),Chord,xoffset,aero center,Section Label,Uni,Skin,-blank-,HP,LP,,,,HP,LP,,,,,,,,,,,,,,,,,,,, -1,0,circular,round,0,2,0.5,0.25,,24.000,1.000,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, -2,4.1789,circular,round,0,2,0.5,0.25,,24.000,1.000,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, -3,8.3578,circular,round,0,2,0.5,0.25,,24.000,1.000,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, -4,12.5367,circular,round,0,2,0.5,0.25,,24.000,1.000,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, -5,16.7156,circular,round,0,2,0.5,0.25,,24.000,1.000,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, -6,20.8945,circular,round,0,2,0.5,0.25,,24.000,1.000,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, -7,25.0734,circular,round,0,2,0.5,0.25,,24.000,1.000,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, -8,29.2523,circular,round,0,2,0.5,0.25,,24.000,1.000,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, -9,33.4312,circular,round,0,2,0.5,0.25,,24.000,1.000,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, -10,37.6101,circular,round,0,2,0.5,0.25,,24.000,1.000,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, -11,41.789,circular,round,0,2,0.5,0.25,,24.000,1.000,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, -,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, -,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, -,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, -,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, -,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, -,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, -,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, -,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, -,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, -,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, -,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, -,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, -,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, -,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, -,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, -,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, -,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, -,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, -,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, -,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, -,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, -,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, -,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, -,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, -,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, -,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, -,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, -,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, -,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, -,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, -,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, -,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, -,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, -,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, -,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, -,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, -,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, -,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, -,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, -,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, \ No newline at end of file diff --git a/examples/SNL17m/data/NuMAD_34m_TowerMaterials.csv b/examples/SNL17m/data/NuMAD_34m_TowerMaterials.csv deleted file mode 100644 index 8527aacb..00000000 --- a/examples/SNL17m/data/NuMAD_34m_TowerMaterials.csv +++ /dev/null @@ -1,11 +0,0 @@ -,,,,Ex,Ey,Ez,Gxy,Gyz,Gxz,prxy,pryz,prxz,,,, -,,Type,Layer Thickness,E11,E22,,G12,,,nu12,,,density,UTS,UCS,Reference -Material ID,,,[mm],[MPa],[MPa],[MPa],[MPa],[MPa],[MPa],[-],[-],[-],[kg/m3],[MPa],[MPa], -1,ELT_5500,orthotropic,1.3,47835,18197,18197,2826,2826,2826,0.3,0.3,0.3,1950,875.634139,-592.949102, -2,EBX_2400,orthotropic,0.61,17183,17183,17183,9202,9202,9202,0.3,0.3,0.3,1900,455.053962,-455.053962, -3,ETLX_2400,orthotropic,0.66,20333,9305,9305,4756,4756,4756,0.3,0.3,0.3,1900,530.896289,-530.896289, -4,Airex_C70_55,orthotropic,1,45,45,69,22,22,22,0.2,0.2,0.2,59,100,100, -5,EBX_2400_x10,orthotropic,0.13,478353,181967,181967,28260,28260,28260,0.3,0.3,0.3,19000,4550.53962,-4550.53962, -6,ETLX_2400_x10,orthotropic,0.06,171825,171825,171825,92019,92019,92019,0.3,0.3,0.3,19000,5308.96289,-5308.96289, -7,Airex_C70_55_x10,orthotropic,0.07,203335,93051,93051,47560,47560,47560,0.2,0.2,0.2,590,0,0, -8,Aluminum_6063_T6_T&C,isotropic,0.5,6.89E+04,6.89E+04,6.89E+04,2.58E+04,2.58E+04,2.58E+04,0.33,0.33,0.33,2700,241,434, diff --git a/examples/SNL17m/data/NuMAD_SNL34mGeomBlades.csv b/examples/SNL17m/data/NuMAD_SNL34mGeomBlades.csv deleted file mode 100644 index 1ea0ccbc..00000000 --- a/examples/SNL17m/data/NuMAD_SNL34mGeomBlades.csv +++ /dev/null @@ -1,33 +0,0 @@ -SNL_34m_Aluminum,,,,# Shear webs ->,11,# of stacks ->,6,Stack ID ->,1,2,3,4,5,6,Segment ID ->,1,2,3,4,5,6,7,8,9,10,11,12,13,14,15,16,17,18,19,20,21,22,23,24,DP Types,1,2,3,4,5,6,7,8,9,10,11,12,13,14,15,16,17,18,19,20,21,22,23,24,1,2,3,4,5,6,7,8,9,10,11,12,13,14,15,16,17,18,19,20,21,22,23,24,,,,,,,,,,,,,,,,,,,,,, -,,,,,,# of segments ->,24,Material ID ->,3,3,3,3,3,3,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,first entry in the CSV list is the exterior blade surface stack,,,,,,,,,,,,,,,,,,,,,,,,SW1,,SW2,,SW3,,SW4,,SW5,,SW6,,SW7,,SW8,,SW9,,SW10,,SW11, -Sta.#,Blade span (m),Airfoil Shape File,TE Type,Twist (deg),Chord,xoffset,aero center,Section Label,Base Skin and Rib,Mid Skin,Zero,Rib Mid,Rib Center,Center Skin,-blank-,HPBay12,HPBay11,HPBay10,HPBay9,HPBay8,HPBay7,HPBay6,HPBay5,HPBay4,HPBay3,HPBay2,HPBay1,LPBay1,LPBay2,LPBay3,LPBay4,LPBay5,LPBay6,LPBay7,LPBay8,LPBay9,LPBay10,LPBay11,LPBay12,,,,,,,,,,,,,,,,,,,,,,,,,,HPBay12,HPBay11,HPBay10,HPBay9,HPBay8,HPBay7,HPBay6,HPBay5,HPBay4,HPBay3,HPBay2,HPBay1,LPBay1,LPBay2,LPBay3,LPBay4,LPBay5,LPBay6,LPBay7,LPBay8,LPBay9,LPBay10,LPBay11,LPBay12,stacks,dps,stacks,,,,,,,,,,,,,,,,,,, -1,0,NACA_0021,sharp,0,1.219,0.3,0.25,R,1,0,0,0,0,0,-1,-0.9167,-0.8333,-0.75,-0.6667,-0.5833,-0.5,-0.4167,-0.3333,-0.25,-0.1667,-0.0833,0,0.0833,0.1667,0.25,0.3333,0.4167,0.5,0.5833,0.6667,0.75,0.8333,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","13,11,11,13","1,","14,10,10,14","1,","15,9,9,15","1,","16,8,8,16","1,","17,7,7,17","1,","18,6,6,18","1,","19,5,5,19","1,","20,4,4,20","1,","21,3,3,21","1,","22,2,2,22","1,","23,1,1,23" -2,3.672615101,NACA_0021,sharp,0,1.219,0.3,0.25,R,1,0,0,0,0,0,-1,-0.9167,-0.8333,-0.75,-0.6667,-0.5833,-0.5,-0.4167,-0.3333,-0.25,-0.1667,-0.0833,0,0.0833,0.1667,0.25,0.3333,0.4167,0.5,0.5833,0.6667,0.75,0.8333,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","13,11,11,13","1,","14,10,10,14","1,","15,9,9,15","1,","16,8,8,16","1,","17,7,7,17","1,","18,6,6,18","1,","19,5,5,19","1,","20,4,4,20","1,","21,3,3,21","1,","22,2,2,22","1,","23,1,1,23" -3,7.344285215,NACA_0021,sharp,0,1.219,0.3,0.25,R,1,0,0,0,0,0,-1,-0.9167,-0.8333,-0.75,-0.6667,-0.5833,-0.5,-0.4167,-0.3333,-0.25,-0.1667,-0.0833,0,0.0833,0.1667,0.25,0.3333,0.4167,0.5,0.5833,0.6667,0.75,0.8333,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","13,11,11,13","1,","14,10,10,14","1,","15,9,9,15","1,","16,8,8,16","1,","17,7,7,17","1,","18,6,6,18","1,","19,5,5,19","1,","20,4,4,20","1,","21,3,3,21","1,","22,2,2,22","1,","23,1,1,23" -4,10.89367149,NACA_0021,sharp,0,1.219,0.3,0.25,RT,1,0,0,0,0,0,-1,-0.9167,-0.8333,-0.75,-0.6667,-0.5833,-0.5,-0.4167,-0.3333,-0.25,-0.1667,-0.0833,0,0.0833,0.1667,0.25,0.3333,0.4167,0.5,0.5833,0.6667,0.75,0.8333,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","13,11,11,13","1,","14,10,10,14","1,","15,9,9,15","1,","16,8,8,16","1,","17,7,7,17","1,","18,6,6,18","1,","19,5,5,19","1,","20,4,4,20","1,","21,3,3,21","1,","22,2,2,22","1,","23,1,1,23" -5,10.9717051,SNL_0018_50,sharp,0,1.067,0.3,0.25,T,0,1,0,1,0,0,-1,-0.9167,-0.9,-0.8,-0.7,-0.6,-0.5,-0.4,-0.3,-0.2,-0.1,-0.0833,0,0.0833,0.1,0.2,0.3,0.4,0.5,0.6,0.7,0.8,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","4,","14,10,10,14","4,","15,9,9,15","4,","16,8,8,16","4,","17,7,7,17","4,","18,6,6,18","4,","19,5,5,19","4,","20,4,4,20","4,","21,3,3,21","4,","22,2,2,22","3,","22,2,2,22","3,","23,1,1,23" -6,13.87890492,SNL_0018_50,sharp,0,1.067,0.3,0.25,T,0,1,0,1,0,0,-1,-0.9167,-0.9,-0.8,-0.7,-0.6,-0.5,-0.4,-0.3,-0.2,-0.1,-0.0833,0,0.0833,0.1,0.2,0.3,0.4,0.5,0.6,0.7,0.8,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","4,","14,10,10,14","4,","15,9,9,15","4,","16,8,8,16","4,","17,7,7,17","4,","18,6,6,18","4,","19,5,5,19","4,","20,4,4,20","4,","21,3,3,21","4,","22,2,2,22","3,","22,2,2,22","3,","23,1,1,23" -7,16.58070907,SNL_0018_50,sharp,0,1.067,0.3,0.25,T,0,1,0,1,0,0,-1,-0.9167,-0.9,-0.8,-0.7,-0.6,-0.5,-0.4,-0.3,-0.2,-0.1,-0.0833,0,0.0833,0.1,0.2,0.3,0.4,0.5,0.6,0.7,0.8,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","4,","14,10,10,14","4,","15,9,9,15","4,","16,8,8,16","4,","17,7,7,17","4,","18,6,6,18","4,","19,5,5,19","4,","20,4,4,20","4,","21,3,3,21","4,","22,2,2,22","3,","22,2,2,22","3,","23,1,1,23" -8,18.16034582,SNL_0018_50,sharp,0,1.067,0.3,0.25,TC,0,1,0,1,0,0,-1,-0.9167,-0.9,-0.8,-0.7,-0.6,-0.5,-0.4,-0.3,-0.2,-0.1,-0.0833,0,0.0833,0.1,0.2,0.3,0.4,0.5,0.6,0.7,0.8,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","4,","14,10,10,14","4,","15,9,9,15","4,","16,8,8,16","4,","17,7,7,17","4,","18,6,6,18","4,","19,5,5,19","4,","20,4,4,20","4,","21,3,3,21","4,","22,2,2,22","3,","22,2,2,22","3,","23,1,1,23" -9,18.21843304,SNL_0018_50,sharp,0,0.914,0.3,0.25,C,0,0,0,0,1,1,-1,-0.9167,-0.9,-0.875,-0.75,-0.625,-0.5,-0.375,-0.25,-0.125,-0.1,-0.0833,0,0.0833,0.1,0.125,0.25,0.375,0.5,0.625,0.75,0.875,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","5,","15,9,9,15","5,","16,8,8,16","5,","17,7,7,17","5,","18,6,6,18","5,","19,5,5,19","5,","20,4,4,20","5,","21,3,3,21","3,","18,2,2,18","3,","19,1,1,19","3,","22,2,2,22","3,","23,1,1,23" -10,19.02368414,SNL_0018_50,sharp,0,0.914,0.3,0.25,C,0,0,0,0,1,1,-1,-0.9167,-0.9,-0.875,-0.75,-0.625,-0.5,-0.375,-0.25,-0.125,-0.1,-0.0833,0,0.0833,0.1,0.125,0.25,0.375,0.5,0.625,0.75,0.875,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","5,","15,9,9,15","5,","16,8,8,16","5,","17,7,7,17","5,","18,6,6,18","5,","19,5,5,19","5,","20,4,4,20","5,","21,3,3,21","3,","18,2,2,18","3,","19,1,1,19","3,","22,2,2,22","3,","23,1,1,23" -11,21.25293416,SNL_0018_50,sharp,0,0.914,0.3,0.25,C,0,0,0,0,1,1,-1,-0.9167,-0.9,-0.875,-0.75,-0.625,-0.5,-0.375,-0.25,-0.125,-0.1,-0.0833,0,0.0833,0.1,0.125,0.25,0.375,0.5,0.625,0.75,0.875,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","5,","15,9,9,15","5,","16,8,8,16","5,","17,7,7,17","5,","18,6,6,18","5,","19,5,5,19","5,","20,4,4,20","5,","21,3,3,21","3,","18,2,2,18","3,","19,1,1,19","3,","22,2,2,22","3,","23,1,1,23" -12,23.36835879,SNL_0018_50,sharp,0,0.914,0.3,0.25,C,0,0,0,0,1,1,-1,-0.9167,-0.9,-0.875,-0.75,-0.625,-0.5,-0.375,-0.25,-0.125,-0.1,-0.0833,0,0.0833,0.1,0.125,0.25,0.375,0.5,0.625,0.75,0.875,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","5,","15,9,9,15","5,","16,8,8,16","5,","17,7,7,17","5,","18,6,6,18","5,","19,5,5,19","5,","20,4,4,20","5,","21,3,3,21","3,","18,2,2,18","3,","19,1,1,19","3,","22,2,2,22","3,","23,1,1,23" -13,25.41318676,SNL_0018_50,sharp,0,0.914,0.3,0.25,C,0,0,0,0,1,1,-1,-0.9167,-0.9,-0.875,-0.75,-0.625,-0.5,-0.375,-0.25,-0.125,-0.1,-0.0833,0,0.0833,0.1,0.125,0.25,0.375,0.5,0.625,0.75,0.875,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","5,","15,9,9,15","5,","16,8,8,16","5,","17,7,7,17","5,","18,6,6,18","5,","19,5,5,19","5,","20,4,4,20","5,","21,3,3,21","3,","18,2,2,18","3,","19,1,1,19","3,","22,2,2,22","3,","23,1,1,23" -14,27.355,SNL_0018_50,sharp,0,0.914,0.3,0.25,C,0,0,0,0,1,1,-1,-0.9167,-0.9,-0.875,-0.75,-0.625,-0.5,-0.375,-0.25,-0.125,-0.1,-0.0833,0,0.0833,0.1,0.125,0.25,0.375,0.5,0.625,0.75,0.875,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","5,","15,9,9,15","5,","16,8,8,16","5,","17,7,7,17","5,","18,6,6,18","5,","19,5,5,19","5,","20,4,4,20","5,","21,3,3,21","3,","18,2,2,18","3,","19,1,1,19","3,","22,2,2,22","3,","23,1,1,23" -15,27.42204788,SNL_0018_50,sharp,0,0.914,0.3,0.25,C,0,0,0,0,1,1,-1,-0.9167,-0.9,-0.875,-0.75,-0.625,-0.5,-0.375,-0.25,-0.125,-0.1,-0.0833,0,0.0833,0.1,0.125,0.25,0.375,0.5,0.625,0.75,0.875,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","5,","15,9,9,15","5,","16,8,8,16","5,","17,7,7,17","5,","18,6,6,18","5,","19,5,5,19","5,","20,4,4,20","5,","21,3,3,21","3,","18,2,2,18","3,","19,1,1,19","3,","22,2,2,22","3,","23,1,1,23" -16,29.4239724,SNL_0018_50,sharp,0,0.914,0.3,0.25,C,0,0,0,0,1,1,-1,-0.9167,-0.9,-0.875,-0.75,-0.625,-0.5,-0.375,-0.25,-0.125,-0.1,-0.0833,0,0.0833,0.1,0.125,0.25,0.375,0.5,0.625,0.75,0.875,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","5,","15,9,9,15","5,","16,8,8,16","5,","17,7,7,17","5,","18,6,6,18","5,","19,5,5,19","5,","20,4,4,20","5,","21,3,3,21","3,","18,2,2,18","3,","19,1,1,19","3,","22,2,2,22","3,","23,1,1,23" -17,31.44591551,SNL_0018_50,sharp,0,0.914,0.3,0.25,C,0,0,0,0,1,1,-1,-0.9167,-0.9,-0.875,-0.75,-0.625,-0.5,-0.375,-0.25,-0.125,-0.1,-0.0833,0,0.0833,0.1,0.125,0.25,0.375,0.5,0.625,0.75,0.875,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","5,","15,9,9,15","5,","16,8,8,16","5,","17,7,7,17","5,","18,6,6,18","5,","19,5,5,19","5,","20,4,4,20","5,","21,3,3,21","3,","18,2,2,18","3,","19,1,1,19","3,","22,2,2,22","3,","23,1,1,23" -18,33.51988932,SNL_0018_50,sharp,0,0.914,0.3,0.25,C,0,0,0,0,1,1,-1,-0.9167,-0.9,-0.875,-0.75,-0.625,-0.5,-0.375,-0.25,-0.125,-0.1,-0.0833,0,0.0833,0.1,0.125,0.25,0.375,0.5,0.625,0.75,0.875,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","5,","15,9,9,15","5,","16,8,8,16","5,","17,7,7,17","5,","18,6,6,18","5,","19,5,5,19","5,","20,4,4,20","5,","21,3,3,21","3,","18,2,2,18","3,","19,1,1,19","3,","22,2,2,22","3,","23,1,1,23" -19,35.68174739,SNL_0018_50,sharp,0,0.914,0.3,0.25,C,0,0,0,0,1,1,-1,-0.9167,-0.9,-0.875,-0.75,-0.625,-0.5,-0.375,-0.25,-0.125,-0.1,-0.0833,0,0.0833,0.1,0.125,0.25,0.375,0.5,0.625,0.75,0.875,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","5,","15,9,9,15","5,","16,8,8,16","5,","17,7,7,17","5,","18,6,6,18","5,","19,5,5,19","5,","20,4,4,20","5,","21,3,3,21","3,","18,2,2,18","3,","19,1,1,19","3,","22,2,2,22","3,","23,1,1,23" -20,37.27556454,SNL_0018_50,sharp,0,0.914,0.3,0.25,TC,0,0,0,0,1,1,-1,-0.9167,-0.9,-0.875,-0.75,-0.625,-0.5,-0.375,-0.25,-0.125,-0.1,-0.0833,0,0.0833,0.1,0.125,0.25,0.375,0.5,0.625,0.75,0.875,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","5,","15,9,9,15","5,","16,8,8,16","5,","17,7,7,17","5,","18,6,6,18","5,","19,5,5,19","5,","20,4,4,20","5,","21,3,3,21","3,","18,2,2,18","3,","19,1,1,19","3,","22,2,2,22","3,","23,1,1,23" -21,37.33686275,SNL_0018_50,sharp,0,1.067,0.3,0.25,T,0,1,0,1,0,0,-1,-0.9167,-0.9,-0.8,-0.7,-0.6,-0.5,-0.4,-0.3,-0.2,-0.1,-0.0833,0,0.0833,0.1,0.2,0.3,0.4,0.5,0.6,0.7,0.8,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","4,","14,10,10,14","4,","15,9,9,15","4,","16,8,8,16","4,","17,7,7,17","4,","18,6,6,18","4,","19,5,5,19","4,","20,4,4,20","4,","21,3,3,21","4,","22,2,2,22","3,","22,2,2,22","3,","23,1,1,23" -22,38.02357633,SNL_0018_50,sharp,0,1.067,0.3,0.25,T,0,1,0,1,0,0,-1,-0.9167,-0.9,-0.8,-0.7,-0.6,-0.5,-0.4,-0.3,-0.2,-0.1,-0.0833,0,0.0833,0.1,0.2,0.3,0.4,0.5,0.6,0.7,0.8,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","4,","14,10,10,14","4,","15,9,9,15","4,","16,8,8,16","4,","17,7,7,17","4,","18,6,6,18","4,","19,5,5,19","4,","20,4,4,20","4,","21,3,3,21","4,","22,2,2,22","3,","22,2,2,22","3,","23,1,1,23" -23,40.5669729,SNL_0018_50,sharp,0,1.067,0.3,0.25,T,0,1,0,1,0,0,-1,-0.9167,-0.9,-0.8,-0.7,-0.6,-0.5,-0.4,-0.3,-0.2,-0.1,-0.0833,0,0.0833,0.1,0.2,0.3,0.4,0.5,0.6,0.7,0.8,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","4,","14,10,10,14","4,","15,9,9,15","4,","16,8,8,16","4,","17,7,7,17","4,","18,6,6,18","4,","19,5,5,19","4,","20,4,4,20","4,","21,3,3,21","4,","22,2,2,22","3,","22,2,2,22","3,","23,1,1,23" -24,43.30266738,SNL_0018_50,sharp,0,1.067,0.3,0.25,T,0,1,0,1,0,0,-1,-0.9167,-0.9,-0.8,-0.7,-0.6,-0.5,-0.4,-0.3,-0.2,-0.1,-0.0833,0,0.0833,0.1,0.2,0.3,0.4,0.5,0.6,0.7,0.8,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","4,","14,10,10,14","4,","15,9,9,15","4,","16,8,8,16","4,","17,7,7,17","4,","18,6,6,18","4,","19,5,5,19","4,","20,4,4,20","4,","21,3,3,21","4,","22,2,2,22","3,","22,2,2,22","3,","23,1,1,23" -25,43.74570399,SNL_0018_50,sharp,0,1.067,0.3,0.25,RT,0,1,0,1,0,0,-1,-0.9167,-0.9,-0.8,-0.7,-0.6,-0.5,-0.4,-0.3,-0.2,-0.1,-0.0833,0,0.0833,0.1,0.2,0.3,0.4,0.5,0.6,0.7,0.8,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","4,","14,10,10,14","4,","15,9,9,15","4,","16,8,8,16","4,","17,7,7,17","4,","18,6,6,18","4,","19,5,5,19","4,","20,4,4,20","4,","21,3,3,21","4,","22,2,2,22","3,","22,2,2,22","3,","23,1,1,23" -26,43.82410891,NACA_0021,sharp,0,1.219,0.3,0.25,R,1,0,0,0,0,0,-1,-0.9167,-0.8333,-0.75,-0.6667,-0.5833,-0.5,-0.4167,-0.3333,-0.25,-0.1667,-0.0833,0,0.0833,0.1667,0.25,0.3333,0.4167,0.5,0.5833,0.6667,0.75,0.8333,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","13,11,11,13","1,","14,10,10,14","1,","15,9,9,15","1,","16,8,8,16","1,","17,7,7,17","1,","18,6,6,18","1,","19,5,5,19","1,","20,4,4,20","1,","21,3,3,21","1,","22,2,2,22","1,","23,1,1,23" -27,46.60132043,NACA_0021,sharp,0,1.219,0.3,0.25,R,1,0,0,0,0,0,-1,-0.9167,-0.8333,-0.75,-0.6667,-0.5833,-0.5,-0.4167,-0.3333,-0.25,-0.1667,-0.0833,0,0.0833,0.1667,0.25,0.3333,0.4167,0.5,0.5833,0.6667,0.75,0.8333,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","13,11,11,13","1,","14,10,10,14","1,","15,9,9,15","1,","16,8,8,16","1,","17,7,7,17","1,","18,6,6,18","1,","19,5,5,19","1,","20,4,4,20","1,","21,3,3,21","1,","22,2,2,22","1,","23,1,1,23" -28,49.9631231,NACA_0021,sharp,0,1.219,0.3,0.25,R,1,0,0,0,0,0,-1,-0.9167,-0.8333,-0.75,-0.6667,-0.5833,-0.5,-0.4167,-0.3333,-0.25,-0.1667,-0.0833,0,0.0833,0.1667,0.25,0.3333,0.4167,0.5,0.5833,0.6667,0.75,0.8333,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","13,11,11,13","1,","14,10,10,14","1,","15,9,9,15","1,","16,8,8,16","1,","17,7,7,17","1,","18,6,6,18","1,","19,5,5,19","1,","20,4,4,20","1,","21,3,3,21","1,","22,2,2,22","1,","23,1,1,23" -29,53.32617545,NACA_0021,sharp,0,1.219,0.3,0.25,R,1,0,0,0,0,0,-1,-0.9167,-0.8333,-0.75,-0.6667,-0.5833,-0.5,-0.4167,-0.3333,-0.25,-0.1667,-0.0833,0,0.0833,0.1667,0.25,0.3333,0.4167,0.5,0.5833,0.6667,0.75,0.8333,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","13,11,11,13","1,","14,10,10,14","1,","15,9,9,15","1,","16,8,8,16","1,","17,7,7,17","1,","18,6,6,18","1,","19,5,5,19","1,","20,4,4,20","1,","21,3,3,21","1,","22,2,2,22","1,","23,1,1,23" -30,56.333,NACA_0021,sharp,0,1.219,0.3,0.25,R,1,0,0,0,0,0,-1,-0.9167,-0.8333,-0.75,-0.6667,-0.5833,-0.5,-0.4167,-0.3333,-0.25,-0.1667,-0.0833,0,0.0833,0.1667,0.25,0.3333,0.4167,0.5,0.5833,0.6667,0.75,0.8333,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","13,11,11,13","1,","14,10,10,14","1,","15,9,9,15","1,","16,8,8,16","1,","17,7,7,17","1,","18,6,6,18","1,","19,5,5,19","1,","20,4,4,20","1,","21,3,3,21","1,","22,2,2,22","1,","23,1,1,23" \ No newline at end of file diff --git a/examples/SNL17m/data/NuMAD_SNL34mGeomStruts.csv b/examples/SNL17m/data/NuMAD_SNL34mGeomStruts.csv deleted file mode 100644 index 28e317f0..00000000 --- a/examples/SNL17m/data/NuMAD_SNL34mGeomStruts.csv +++ /dev/null @@ -1,9 +0,0 @@ -SNL_34m_Aluminum,,,,# Shear webs ->,11,# of stacks ->,6,Stack ID ->,1,2,3,4,5,6,Segment ID ->,1,2,3,4,5,6,7,8,9,10,11,12,13,14,15,16,17,18,19,20,21,22,23,24,DP Types,1,2,3,4,5,6,7,8,9,10,11,12,13,14,15,16,17,18,19,20,21,22,23,24,1,2,3,4,5,6,7,8,9,10,11,12,13,14,15,16,17,18,19,20,21,22,23,24,,,,,,,,,,,,,,,,,,,,,, -,,,,,,# of segments ->,24,Material ID ->,2,1,1,1,1,1,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,first entry in the CSV list is the exterior blade surface stack,,,,,,,,,,,,,,,,,,,,,,,,SW1,,SW2,,SW3,,SW4,,SW5,,SW6,,SW7,,SW8,,SW9,,SW10,,SW11, -Sta.#,Blade span (m),Airfoil Shape File,TE Type,Twist (deg),Chord,xoffset,aero center,Section Label,Base Skin and Rib,Mid Skin,Zero,Rib Mid,Rib Center,Center Skin,-blank-,HPBay12,HPBay11,HPBay10,HPBay9,HPBay8,HPBay7,HPBay6,HPBay5,HPBay4,HPBay3,HPBay2,HPBay1,LPBay1,LPBay2,LPBay3,LPBay4,LPBay5,LPBay6,LPBay7,LPBay8,LPBay9,LPBay10,LPBay11,LPBay12,,,,,,,,,,,,,,,,,,,,,,,,,,HPBay12,HPBay11,HPBay10,HPBay9,HPBay8,HPBay7,HPBay6,HPBay5,HPBay4,HPBay3,HPBay2,HPBay1,LPBay1,LPBay2,LPBay3,LPBay4,LPBay5,LPBay6,LPBay7,LPBay8,LPBay9,LPBay10,LPBay11,LPBay12,stacks,dps,stacks,,,,,,,,,,,,,,,,,,, -1,0,circular,sharp,0,0.05,0.3,0.25,R,1,0,0,0,0,0,-1,-0.9167,-0.8333,-0.75,-0.6667,-0.5833,-0.5,-0.4167,-0.3333,-0.25,-0.1667,-0.0833,0,0.0833,0.1667,0.25,0.3333,0.4167,0.5,0.5833,0.6667,0.75,0.8333,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","13,11,11,13","1,","14,10,10,14","1,","15,9,9,15","1,","16,8,8,16","1,","17,7,7,17","1,","18,6,6,18","1,","19,5,5,19","1,","20,4,4,20","1,","21,3,3,21","1,","22,2,2,22","1,","23,1,1,23" -2,0.5,circular,sharp,0,0.05,0.3,0.25,R,1,0,0,0,0,0,-1,-0.9167,-0.8333,-0.75,-0.6667,-0.5833,-0.5,-0.4167,-0.3333,-0.25,-0.1667,-0.0833,0,0.0833,0.1667,0.25,0.3333,0.4167,0.5,0.5833,0.6667,0.75,0.8333,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","13,11,11,13","1,","14,10,10,14","1,","15,9,9,15","1,","16,8,8,16","1,","17,7,7,17","1,","18,6,6,18","1,","19,5,5,19","1,","20,4,4,20","1,","21,3,3,21","1,","22,2,2,22","1,","23,1,1,23" -3,0.97,circular,sharp,0,0.05,0.3,0.25,R,1,0,0,0,0,0,-1,-0.9167,-0.8333,-0.75,-0.6667,-0.5833,-0.5,-0.4167,-0.3333,-0.25,-0.1667,-0.0833,0,0.0833,0.1667,0.25,0.3333,0.4167,0.5,0.5833,0.6667,0.75,0.8333,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","13,11,11,13","1,","14,10,10,14","1,","15,9,9,15","1,","16,8,8,16","1,","17,7,7,17","1,","18,6,6,18","1,","19,5,5,19","1,","20,4,4,20","1,","21,3,3,21","1,","22,2,2,22","1,","23,1,1,23" -4,0.98,circular,sharp,0,0.05,0.3,0.25,R,1,0,0,0,0,0,-1,-0.9167,-0.8333,-0.75,-0.6667,-0.5833,-0.5,-0.4167,-0.3333,-0.25,-0.1667,-0.0833,0,0.0833,0.1667,0.25,0.3333,0.4167,0.5,0.5833,0.6667,0.75,0.8333,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","13,11,11,13","1,","14,10,10,14","1,","15,9,9,15","1,","16,8,8,16","1,","17,7,7,17","1,","18,6,6,18","1,","19,5,5,19","1,","20,4,4,20","1,","21,3,3,21","1,","22,2,2,22","1,","23,1,1,23" -5,0.99,circular,sharp,0,0.05,0.3,0.25,R,5,0,0,0,0,0,-1,-0.9167,-0.8333,-0.75,-0.6667,-0.5833,-0.5,-0.4167,-0.3333,-0.25,-0.1667,-0.0833,0,0.0833,0.1667,0.25,0.3333,0.4167,0.5,0.5833,0.6667,0.75,0.8333,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","13,11,11,13","1,","14,10,10,14","1,","15,9,9,15","1,","16,8,8,16","1,","17,7,7,17","1,","18,6,6,18","1,","19,5,5,19","1,","20,4,4,20","1,","21,3,3,21","1,","22,2,2,22","1,","23,1,1,23" -6,1,circular,sharp,0,0.05,0.3,0.25,R,5,0,0,0,0,0,-1,-0.9167,-0.8333,-0.75,-0.6667,-0.5833,-0.5,-0.4167,-0.3333,-0.25,-0.1667,-0.0833,0,0.0833,0.1667,0.25,0.3333,0.4167,0.5,0.5833,0.6667,0.75,0.8333,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","13,11,11,13","1,","14,10,10,14","1,","15,9,9,15","1,","16,8,8,16","1,","17,7,7,17","1,","18,6,6,18","1,","19,5,5,19","1,","20,4,4,20","1,","21,3,3,21","1,","22,2,2,22","1,","23,1,1,23" \ No newline at end of file diff --git a/examples/SNL17m/data/blades_NuMAD.csv b/examples/SNL17m/data/blades_NuMAD.csv new file mode 100644 index 00000000..f650633a --- /dev/null +++ b/examples/SNL17m/data/blades_NuMAD.csv @@ -0,0 +1,33 @@ +SNL_34m_Aluminum,,,,# Shear webs ->,11,# of stacks ->,6,Stack ID ->,1,2,3,4,5,6,Segment ID ->,1,2,3,4,5,6,7,8,9,10,11,12,13,14,15,16,17,18,19,20,21,22,23,24,DP Types,1,2,3,4,5,6,7,8,9,10,11,12,13,14,15,16,17,18,19,20,21,22,23,24,1,2,3,4,5,6,7,8,9,10,11,12,13,14,15,16,17,18,19,20,21,22,23,24,,,,,,,,,,,,,,,,,,,,,, +,,,,,,# of segments ->,24,Material ID ->,1,1,1,1,1,1,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,first entry in the CSV list is the exterior blade surface stack,,,,,,,,,,,,,,,,,,,,,,,,SW1,,SW2,,SW3,,SW4,,SW5,,SW6,,SW7,,SW8,,SW9,,SW10,,SW11, +Sta.#,Blade span (m),Airfoil Shape File,TE Type,Twist (deg),Chord,xoffset,aero center,Section Label,Base Skin and Rib,Mid Skin,Zero,Rib Mid,Rib Center,Center Skin,-blank-,HPBay12,HPBay11,HPBay10,HPBay9,HPBay8,HPBay7,HPBay6,HPBay5,HPBay4,HPBay3,HPBay2,HPBay1,LPBay1,LPBay2,LPBay3,LPBay4,LPBay5,LPBay6,LPBay7,LPBay8,LPBay9,LPBay10,LPBay11,LPBay12,,,,,,,,,,,,,,,,,,,,,,,,,,HPBay12,HPBay11,HPBay10,HPBay9,HPBay8,HPBay7,HPBay6,HPBay5,HPBay4,HPBay3,HPBay2,HPBay1,LPBay1,LPBay2,LPBay3,LPBay4,LPBay5,LPBay6,LPBay7,LPBay8,LPBay9,LPBay10,LPBay11,LPBay12,stacks,dps,stacks,,,,,,,,,,,,,,,,,,, +1,0,NACA_0021,sharp,0,0.5,0.3,0.25,R,30,0,0,0,0,0,-1,-0.9167,-0.8333,-0.75,-0.6667,-0.5833,-0.5,-0.4167,-0.3333,-0.25,-0.1667,-0.0833,0,0.0833,0.1667,0.25,0.3333,0.4167,0.5,0.5833,0.6667,0.75,0.8333,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","13,11,11,13","1,","14,10,10,14","1,","15,9,9,15","1,","16,8,8,16","1,","17,7,7,17","1,","18,6,6,18","1,","19,5,5,19","1,","20,4,4,20","1,","21,3,3,21","1,","22,2,2,22","1,","23,1,1,23" +2,3.672615101,NACA_0021,sharp,0,0.5,0.3,0.25,R,30,0,0,0,0,0,-1,-0.9167,-0.8333,-0.75,-0.6667,-0.5833,-0.5,-0.4167,-0.3333,-0.25,-0.1667,-0.0833,0,0.0833,0.1667,0.25,0.3333,0.4167,0.5,0.5833,0.6667,0.75,0.8333,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","13,11,11,13","1,","14,10,10,14","1,","15,9,9,15","1,","16,8,8,16","1,","17,7,7,17","1,","18,6,6,18","1,","19,5,5,19","1,","20,4,4,20","1,","21,3,3,21","1,","22,2,2,22","1,","23,1,1,23" +3,7.344285215,NACA_0021,sharp,0,0.5,0.3,0.25,R,30,0,0,0,0,0,-1,-0.9167,-0.8333,-0.75,-0.6667,-0.5833,-0.5,-0.4167,-0.3333,-0.25,-0.1667,-0.0833,0,0.0833,0.1667,0.25,0.3333,0.4167,0.5,0.5833,0.6667,0.75,0.8333,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","13,11,11,13","1,","14,10,10,14","1,","15,9,9,15","1,","16,8,8,16","1,","17,7,7,17","1,","18,6,6,18","1,","19,5,5,19","1,","20,4,4,20","1,","21,3,3,21","1,","22,2,2,22","1,","23,1,1,23" +4,10.89367149,NACA_0021,sharp,0,0.5,0.3,0.25,RT,30,0,0,0,0,0,-1,-0.9167,-0.8333,-0.75,-0.6667,-0.5833,-0.5,-0.4167,-0.3333,-0.25,-0.1667,-0.0833,0,0.0833,0.1667,0.25,0.3333,0.4167,0.5,0.5833,0.6667,0.75,0.8333,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","13,11,11,13","1,","14,10,10,14","1,","15,9,9,15","1,","16,8,8,16","1,","17,7,7,17","1,","18,6,6,18","1,","19,5,5,19","1,","20,4,4,20","1,","21,3,3,21","1,","22,2,2,22","1,","23,1,1,23" +5,10.9717051,NACA_0021,sharp,0,0.5,0.3,0.25,T,0,30,0,30,0,0,-1,-0.9167,-0.9,-0.8,-0.7,-0.6,-0.5,-0.4,-0.3,-0.2,-0.1,-0.0833,0,0.0833,0.1,0.2,0.3,0.4,0.5,0.6,0.7,0.8,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","4,","14,10,10,14","4,","15,9,9,15","4,","16,8,8,16","4,","17,7,7,17","4,","18,6,6,18","4,","19,5,5,19","4,","20,4,4,20","4,","21,3,3,21","4,","22,2,2,22","3,","22,2,2,22","3,","23,1,1,23" +6,13.87890492,NACA_0021,sharp,0,0.5,0.3,0.25,T,0,30,0,30,0,0,-1,-0.9167,-0.9,-0.8,-0.7,-0.6,-0.5,-0.4,-0.3,-0.2,-0.1,-0.0833,0,0.0833,0.1,0.2,0.3,0.4,0.5,0.6,0.7,0.8,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","4,","14,10,10,14","4,","15,9,9,15","4,","16,8,8,16","4,","17,7,7,17","4,","18,6,6,18","4,","19,5,5,19","4,","20,4,4,20","4,","21,3,3,21","4,","22,2,2,22","3,","22,2,2,22","3,","23,1,1,23" +7,16.58070907,NACA_0021,sharp,0,0.5,0.3,0.25,T,0,30,0,30,0,0,-1,-0.9167,-0.9,-0.8,-0.7,-0.6,-0.5,-0.4,-0.3,-0.2,-0.1,-0.0833,0,0.0833,0.1,0.2,0.3,0.4,0.5,0.6,0.7,0.8,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","4,","14,10,10,14","4,","15,9,9,15","4,","16,8,8,16","4,","17,7,7,17","4,","18,6,6,18","4,","19,5,5,19","4,","20,4,4,20","4,","21,3,3,21","4,","22,2,2,22","3,","22,2,2,22","3,","23,1,1,23" +8,18.16034582,NACA_0021,sharp,0,0.5,0.3,0.25,TC,0,30,0,30,0,0,-1,-0.9167,-0.9,-0.8,-0.7,-0.6,-0.5,-0.4,-0.3,-0.2,-0.1,-0.0833,0,0.0833,0.1,0.2,0.3,0.4,0.5,0.6,0.7,0.8,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","4,","14,10,10,14","4,","15,9,9,15","4,","16,8,8,16","4,","17,7,7,17","4,","18,6,6,18","4,","19,5,5,19","4,","20,4,4,20","4,","21,3,3,21","4,","22,2,2,22","3,","22,2,2,22","3,","23,1,1,23" +9,18.21843304,NACA_0021,sharp,0,0.5,0.3,0.25,C,0,0,0,0,30,30,-1,-0.9167,-0.9,-0.875,-0.75,-0.625,-0.5,-0.375,-0.25,-0.125,-0.1,-0.0833,0,0.0833,0.1,0.125,0.25,0.375,0.5,0.625,0.75,0.875,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","5,","15,9,9,15","5,","16,8,8,16","5,","17,7,7,17","5,","18,6,6,18","5,","19,5,5,19","5,","20,4,4,20","5,","21,3,3,21","3,","18,2,2,18","3,","19,1,1,19","3,","22,2,2,22","3,","23,1,1,23" +10,19.02368414,NACA_0021,sharp,0,0.5,0.3,0.25,C,0,0,0,0,30,30,-1,-0.9167,-0.9,-0.875,-0.75,-0.625,-0.5,-0.375,-0.25,-0.125,-0.1,-0.0833,0,0.0833,0.1,0.125,0.25,0.375,0.5,0.625,0.75,0.875,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","5,","15,9,9,15","5,","16,8,8,16","5,","17,7,7,17","5,","18,6,6,18","5,","19,5,5,19","5,","20,4,4,20","5,","21,3,3,21","3,","18,2,2,18","3,","19,1,1,19","3,","22,2,2,22","3,","23,1,1,23" +11,21.25293416,NACA_0021,sharp,0,0.5,0.3,0.25,C,0,0,0,0,30,30,-1,-0.9167,-0.9,-0.875,-0.75,-0.625,-0.5,-0.375,-0.25,-0.125,-0.1,-0.0833,0,0.0833,0.1,0.125,0.25,0.375,0.5,0.625,0.75,0.875,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","5,","15,9,9,15","5,","16,8,8,16","5,","17,7,7,17","5,","18,6,6,18","5,","19,5,5,19","5,","20,4,4,20","5,","21,3,3,21","3,","18,2,2,18","3,","19,1,1,19","3,","22,2,2,22","3,","23,1,1,23" +12,23.36835879,NACA_0021,sharp,0,0.5,0.3,0.25,C,0,0,0,0,30,30,-1,-0.9167,-0.9,-0.875,-0.75,-0.625,-0.5,-0.375,-0.25,-0.125,-0.1,-0.0833,0,0.0833,0.1,0.125,0.25,0.375,0.5,0.625,0.75,0.875,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","5,","15,9,9,15","5,","16,8,8,16","5,","17,7,7,17","5,","18,6,6,18","5,","19,5,5,19","5,","20,4,4,20","5,","21,3,3,21","3,","18,2,2,18","3,","19,1,1,19","3,","22,2,2,22","3,","23,1,1,23" +13,25.41318676,NACA_0021,sharp,0,0.5,0.3,0.25,C,0,0,0,0,30,30,-1,-0.9167,-0.9,-0.875,-0.75,-0.625,-0.5,-0.375,-0.25,-0.125,-0.1,-0.0833,0,0.0833,0.1,0.125,0.25,0.375,0.5,0.625,0.75,0.875,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","5,","15,9,9,15","5,","16,8,8,16","5,","17,7,7,17","5,","18,6,6,18","5,","19,5,5,19","5,","20,4,4,20","5,","21,3,3,21","3,","18,2,2,18","3,","19,1,1,19","3,","22,2,2,22","3,","23,1,1,23" +14,27.355,NACA_0021,sharp,0,0.5,0.3,0.25,C,0,0,0,0,30,30,-1,-0.9167,-0.9,-0.875,-0.75,-0.625,-0.5,-0.375,-0.25,-0.125,-0.1,-0.0833,0,0.0833,0.1,0.125,0.25,0.375,0.5,0.625,0.75,0.875,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","5,","15,9,9,15","5,","16,8,8,16","5,","17,7,7,17","5,","18,6,6,18","5,","19,5,5,19","5,","20,4,4,20","5,","21,3,3,21","3,","18,2,2,18","3,","19,1,1,19","3,","22,2,2,22","3,","23,1,1,23" +15,27.42204788,NACA_0021,sharp,0,0.5,0.3,0.25,C,0,0,0,0,30,30,-1,-0.9167,-0.9,-0.875,-0.75,-0.625,-0.5,-0.375,-0.25,-0.125,-0.1,-0.0833,0,0.0833,0.1,0.125,0.25,0.375,0.5,0.625,0.75,0.875,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","5,","15,9,9,15","5,","16,8,8,16","5,","17,7,7,17","5,","18,6,6,18","5,","19,5,5,19","5,","20,4,4,20","5,","21,3,3,21","3,","18,2,2,18","3,","19,1,1,19","3,","22,2,2,22","3,","23,1,1,23" +16,29.4239724,NACA_0021,sharp,0,0.5,0.3,0.25,C,0,0,0,0,30,30,-1,-0.9167,-0.9,-0.875,-0.75,-0.625,-0.5,-0.375,-0.25,-0.125,-0.1,-0.0833,0,0.0833,0.1,0.125,0.25,0.375,0.5,0.625,0.75,0.875,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","5,","15,9,9,15","5,","16,8,8,16","5,","17,7,7,17","5,","18,6,6,18","5,","19,5,5,19","5,","20,4,4,20","5,","21,3,3,21","3,","18,2,2,18","3,","19,1,1,19","3,","22,2,2,22","3,","23,1,1,23" +17,31.44591551,NACA_0021,sharp,0,0.5,0.3,0.25,C,0,0,0,0,30,30,-1,-0.9167,-0.9,-0.875,-0.75,-0.625,-0.5,-0.375,-0.25,-0.125,-0.1,-0.0833,0,0.0833,0.1,0.125,0.25,0.375,0.5,0.625,0.75,0.875,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","5,","15,9,9,15","5,","16,8,8,16","5,","17,7,7,17","5,","18,6,6,18","5,","19,5,5,19","5,","20,4,4,20","5,","21,3,3,21","3,","18,2,2,18","3,","19,1,1,19","3,","22,2,2,22","3,","23,1,1,23" +18,33.51988932,NACA_0021,sharp,0,0.5,0.3,0.25,C,0,0,0,0,30,30,-1,-0.9167,-0.9,-0.875,-0.75,-0.625,-0.5,-0.375,-0.25,-0.125,-0.1,-0.0833,0,0.0833,0.1,0.125,0.25,0.375,0.5,0.625,0.75,0.875,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","5,","15,9,9,15","5,","16,8,8,16","5,","17,7,7,17","5,","18,6,6,18","5,","19,5,5,19","5,","20,4,4,20","5,","21,3,3,21","3,","18,2,2,18","3,","19,1,1,19","3,","22,2,2,22","3,","23,1,1,23" +19,35.68174739,NACA_0021,sharp,0,0.5,0.3,0.25,C,0,0,0,0,30,30,-1,-0.9167,-0.9,-0.875,-0.75,-0.625,-0.5,-0.375,-0.25,-0.125,-0.1,-0.0833,0,0.0833,0.1,0.125,0.25,0.375,0.5,0.625,0.75,0.875,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","5,","15,9,9,15","5,","16,8,8,16","5,","17,7,7,17","5,","18,6,6,18","5,","19,5,5,19","5,","20,4,4,20","5,","21,3,3,21","3,","18,2,2,18","3,","19,1,1,19","3,","22,2,2,22","3,","23,1,1,23" +20,37.27556454,NACA_0021,sharp,0,0.5,0.3,0.25,TC,0,0,0,0,30,30,-1,-0.9167,-0.9,-0.875,-0.75,-0.625,-0.5,-0.375,-0.25,-0.125,-0.1,-0.0833,0,0.0833,0.1,0.125,0.25,0.375,0.5,0.625,0.75,0.875,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","6,","5,","15,9,9,15","5,","16,8,8,16","5,","17,7,7,17","5,","18,6,6,18","5,","19,5,5,19","5,","20,4,4,20","5,","21,3,3,21","3,","18,2,2,18","3,","19,1,1,19","3,","22,2,2,22","3,","23,1,1,23" +21,37.33686275,NACA_0021,sharp,0,0.5,0.3,0.25,T,0,30,0,30,0,0,-1,-0.9167,-0.9,-0.8,-0.7,-0.6,-0.5,-0.4,-0.3,-0.2,-0.1,-0.0833,0,0.0833,0.1,0.2,0.3,0.4,0.5,0.6,0.7,0.8,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","4,","14,10,10,14","4,","15,9,9,15","4,","16,8,8,16","4,","17,7,7,17","4,","18,6,6,18","4,","19,5,5,19","4,","20,4,4,20","4,","21,3,3,21","4,","22,2,2,22","3,","22,2,2,22","3,","23,1,1,23" +22,38.02357633,NACA_0021,sharp,0,0.5,0.3,0.25,T,0,30,0,30,0,0,-1,-0.9167,-0.9,-0.8,-0.7,-0.6,-0.5,-0.4,-0.3,-0.2,-0.1,-0.0833,0,0.0833,0.1,0.2,0.3,0.4,0.5,0.6,0.7,0.8,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","4,","14,10,10,14","4,","15,9,9,15","4,","16,8,8,16","4,","17,7,7,17","4,","18,6,6,18","4,","19,5,5,19","4,","20,4,4,20","4,","21,3,3,21","4,","22,2,2,22","3,","22,2,2,22","3,","23,1,1,23" +23,40.5669729,NACA_0021,sharp,0,0.5,0.3,0.25,T,0,30,0,30,0,0,-1,-0.9167,-0.9,-0.8,-0.7,-0.6,-0.5,-0.4,-0.3,-0.2,-0.1,-0.0833,0,0.0833,0.1,0.2,0.3,0.4,0.5,0.6,0.7,0.8,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","4,","14,10,10,14","4,","15,9,9,15","4,","16,8,8,16","4,","17,7,7,17","4,","18,6,6,18","4,","19,5,5,19","4,","20,4,4,20","4,","21,3,3,21","4,","22,2,2,22","3,","22,2,2,22","3,","23,1,1,23" +24,43.30266738,NACA_0021,sharp,0,0.5,0.3,0.25,T,0,30,0,30,0,0,-1,-0.9167,-0.9,-0.8,-0.7,-0.6,-0.5,-0.4,-0.3,-0.2,-0.1,-0.0833,0,0.0833,0.1,0.2,0.3,0.4,0.5,0.6,0.7,0.8,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","4,","14,10,10,14","4,","15,9,9,15","4,","16,8,8,16","4,","17,7,7,17","4,","18,6,6,18","4,","19,5,5,19","4,","20,4,4,20","4,","21,3,3,21","4,","22,2,2,22","3,","22,2,2,22","3,","23,1,1,23" +25,43.74570399,NACA_0021,sharp,0,0.5,0.3,0.25,RT,0,30,0,30,0,0,-1,-0.9167,-0.9,-0.8,-0.7,-0.6,-0.5,-0.4,-0.3,-0.2,-0.1,-0.0833,0,0.0833,0.1,0.2,0.3,0.4,0.5,0.6,0.7,0.8,0.9,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","2,","4,","14,10,10,14","4,","15,9,9,15","4,","16,8,8,16","4,","17,7,7,17","4,","18,6,6,18","4,","19,5,5,19","4,","20,4,4,20","4,","21,3,3,21","4,","22,2,2,22","3,","22,2,2,22","3,","23,1,1,23" +26,43.82410891,NACA_0021,sharp,0,0.5,0.3,0.25,R,30,0,0,0,0,0,-1,-0.9167,-0.8333,-0.75,-0.6667,-0.5833,-0.5,-0.4167,-0.3333,-0.25,-0.1667,-0.0833,0,0.0833,0.1667,0.25,0.3333,0.4167,0.5,0.5833,0.6667,0.75,0.8333,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","13,11,11,13","1,","14,10,10,14","1,","15,9,9,15","1,","16,8,8,16","1,","17,7,7,17","1,","18,6,6,18","1,","19,5,5,19","1,","20,4,4,20","1,","21,3,3,21","1,","22,2,2,22","1,","23,1,1,23" +27,46.60132043,NACA_0021,sharp,0,0.5,0.3,0.25,R,30,0,0,0,0,0,-1,-0.9167,-0.8333,-0.75,-0.6667,-0.5833,-0.5,-0.4167,-0.3333,-0.25,-0.1667,-0.0833,0,0.0833,0.1667,0.25,0.3333,0.4167,0.5,0.5833,0.6667,0.75,0.8333,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","13,11,11,13","1,","14,10,10,14","1,","15,9,9,15","1,","16,8,8,16","1,","17,7,7,17","1,","18,6,6,18","1,","19,5,5,19","1,","20,4,4,20","1,","21,3,3,21","1,","22,2,2,22","1,","23,1,1,23" +28,49.9631231,NACA_0021,sharp,0,0.5,0.3,0.25,R,30,0,0,0,0,0,-1,-0.9167,-0.8333,-0.75,-0.6667,-0.5833,-0.5,-0.4167,-0.3333,-0.25,-0.1667,-0.0833,0,0.0833,0.1667,0.25,0.3333,0.4167,0.5,0.5833,0.6667,0.75,0.8333,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","13,11,11,13","1,","14,10,10,14","1,","15,9,9,15","1,","16,8,8,16","1,","17,7,7,17","1,","18,6,6,18","1,","19,5,5,19","1,","20,4,4,20","1,","21,3,3,21","1,","22,2,2,22","1,","23,1,1,23" +29,53.32617545,NACA_0021,sharp,0,0.5,0.3,0.25,R,30,0,0,0,0,0,-1,-0.9167,-0.8333,-0.75,-0.6667,-0.5833,-0.5,-0.4167,-0.3333,-0.25,-0.1667,-0.0833,0,0.0833,0.1667,0.25,0.3333,0.4167,0.5,0.5833,0.6667,0.75,0.8333,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","13,11,11,13","1,","14,10,10,14","1,","15,9,9,15","1,","16,8,8,16","1,","17,7,7,17","1,","18,6,6,18","1,","19,5,5,19","1,","20,4,4,20","1,","21,3,3,21","1,","22,2,2,22","1,","23,1,1,23" +30,56.333,NACA_0021,sharp,0,0.5,0.3,0.25,R,30,0,0,0,0,0,-1,-0.9167,-0.8333,-0.75,-0.6667,-0.5833,-0.5,-0.4167,-0.3333,-0.25,-0.1667,-0.0833,0,0.0833,0.1667,0.25,0.3333,0.4167,0.5,0.5833,0.6667,0.75,0.8333,0.9167,1,,,,,,,,,,,,,,,,,,,,,,,,,,"1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","1,","13,11,11,13","1,","14,10,10,14","1,","15,9,9,15","1,","16,8,8,16","1,","17,7,7,17","1,","18,6,6,18","1,","19,5,5,19","1,","20,4,4,20","1,","21,3,3,21","1,","22,2,2,22","1,","23,1,1,23" \ No newline at end of file diff --git a/examples/SNL17m/data/NuMAD_SNL34mMaterials.csv b/examples/SNL17m/data/materials_NuMAD.csv similarity index 62% rename from examples/SNL17m/data/NuMAD_SNL34mMaterials.csv rename to examples/SNL17m/data/materials_NuMAD.csv index 4c74a5ad..f7ea3fd8 100644 --- a/examples/SNL17m/data/NuMAD_SNL34mMaterials.csv +++ b/examples/SNL17m/data/materials_NuMAD.csv @@ -1,6 +1,7 @@ -,,,,Ex,Ey,Ez,Gxy,Gyz,Gxz,prxy,pryz,prxz,,,,,,,,,,,,,,,,,,,,, -,,Type,Layer Thickness,E11,E22,,G12,,,nu12,,,density,UTSx,UCSx,UTSy,UCSy,UTSz,UCSz,Cost,Reference,,,,,,,,,,,, -Material ID,,,[mm],[MPa],[MPa],[MPa],[MPa],[MPa],[MPa],[-],[-],[-],[kg/m3],[MPa],[MPa],[MPa],[MPa],[MPa],[MPa],[$/kg],,,,,,,,,,,,, +,,,,Ex,Ey,Ez,Gxy,Gyz,Gxz,prxy,pryz,prxz,,,,,,,,,,,,,,,,,,,,,, +,,Type,Layer Thickness,E11,E22,,G12,,,nu12,,,density,UTSx,UCSx,UTSy,UCSy,UTSz,UCSz,Cost,Reference,,,,,,,,,,,,, +Material ID,,,[mm],[MPa],[MPa],[MPa],[MPa],[MPa],[MPa],[-],[-],[-],[kg/m3],[MPa],[MPa],[MPa],[MPa],[MPa],[MPa],[$/kg],,,,,,,,,,,,,, 1,Aluminum_6061_T6,isotropic,1.0,6.89E+04,6.89E+04,6.89E+04,2.58E+04,2.58E+04,2.58E+04,.33,.33,.33,2700,270,240,270,240,270,240,11.0,,310,250,200,150,100,0,0,1,2,4,6,20,1 -2,steel,orthotropic,1,199948,199948,199948,76877,76877,76877,0.3,0.3,0.3,7861.092935,420,250,420,250,420,250,1.0,,420,415,375,275,190,0.0,0,1,2,4,6,20 -3,Mithril,isotropic,1.0,6.89E+10,6.89E+10,6.89E+10,2.58E+10,2.58E+10,2.58E+10,.33,.33,.33,0.00001,27000,24000,27000,24000,27000,24000,1e10,,31000,25000,20000,15000,10000,0,0,1,2,4,6,20,1 \ No newline at end of file +2,steel,orthotropic,1,199948,199948,199948,76877,76877,76877,0.3,0.3,0.3,7861.092935,420,250,420,250,420,250,1.0,,420,415,375,275,190,0.0,0,1,2,4,6,20, +3,Mithril,isotropic,1.0,6.89E+10,6.89E+10,6.89E+10,2.58E+10,2.58E+10,2.58E+10,.33,.33,.33,0.00001,27000,24000,27000,24000,27000,24000,1e10,,31000,25000,20000,15000,10000,0,0,1,2,4,6,20,1 +4,steel_cable,orthotropic,1,1.72E+05,1.72E+05,1.72E+05,76877,76877,76877,0.3,0.3,0.3,8010.08,1409,1409,1409,1409,1409,1409,1.0,,1409,1200,800,400,200,0.0,0,1,2,4,6,20, \ No newline at end of file diff --git a/examples/SNL17m/data/struts_NuMAD.csv b/examples/SNL17m/data/struts_NuMAD.csv new file mode 100644 index 00000000..f27445fd --- /dev/null +++ b/examples/SNL17m/data/struts_NuMAD.csv @@ -0,0 +1,8 @@ +SNL_34m_Glass_BPE,,,,# Shear webs ->,0,# of stacks ->,2,Stack ID ->,1,2,Segment ID ->,1,10,DP Types,1,2,1,2,,,,,,,,,,,,,,,,,,,, +,,,,,,# of segments ->,2,Material ID ->,4,4,,,,,,,first entry in the CSV list is the exterior blade surface stack,,,,,,,,,,,,,,,,,,,,, +Sta.#,Blade span (m),Airfoil Shape File,TE Type,Twist (deg),Chord,xoffset,aero center,Section Label,center,Skin,-blank-,HP,LP,,,,HP,LP,,,,,,,,,,,,,,,,,,,, +1,0,circular,round,0,0.011,0.5,0.5,,11,0.0000001,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, +2,0.25,circular,round,0,0.011,0.5,0.5,,11,0.0000001,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, +3,0.5,circular,round,0,0.011,0.5,0.5,,11,0.0000001,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, +4,0.75,circular,round,0,0.011,0.5,0.5,,11,0.0000001,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, +5,1.0,circular,round,0,0.011,0.5,0.5,,11,0.0000001,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, \ No newline at end of file diff --git a/examples/SNL17m/data/tower_NuMAD.csv b/examples/SNL17m/data/tower_NuMAD.csv new file mode 100644 index 00000000..8c25caee --- /dev/null +++ b/examples/SNL17m/data/tower_NuMAD.csv @@ -0,0 +1,14 @@ +SNL_34m_Glass_BPE,,,,# Shear webs ->,0,# of stacks ->,2,Stack ID ->,1,2,Segment ID ->,1,10,DP Types,1,2,1,2,,,,,,,,,,,,,,,,,,,, +,,,,,,# of segments ->,2,Material ID ->,1,1,,,,,,,first entry in the CSV list is the exterior blade surface stack,,,,,,,,,,,,,,,,,,,,, +Sta.#,Blade span (m),Airfoil Shape File,TE Type,Twist (deg),Chord,xoffset,aero center,Section Label,Uni,Skin,-blank-,HP,LP,,,,HP,LP,,,,,,,,,,,,,,,,,,,, +1,0,circular,round,0,1.0,0.5,0.25,,24.000,1.000,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, +2,4.1789,circular,round,0,1.0,0.5,0.25,,24.000,1.000,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, +3,8.3578,circular,round,0,1.0,0.5,0.25,,24.000,1.000,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, +4,12.5367,circular,round,0,1.0,0.5,0.25,,24.000,1.000,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, +5,16.7156,circular,round,0,1.0,0.5,0.25,,24.000,1.000,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, +6,20.8945,circular,round,0,1.0,0.5,0.25,,24.000,1.000,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, +7,25.0734,circular,round,0,1.0,0.5,0.25,,24.000,1.000,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, +8,29.2523,circular,round,0,1.0,0.5,0.25,,24.000,1.000,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, +9,33.4312,circular,round,0,1.0,0.5,0.25,,24.000,1.000,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, +10,37.6101,circular,round,0,1.0,0.5,0.25,,24.000,1.000,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, +11,41.789,circular,round,0,1.0,0.5,0.25,,24.000,1.000,-1.0000,0.0000,1.0000,,,,"2,1,2","2,1,2",,,,,,,,,,,,,,,,,,,, \ No newline at end of file diff --git a/examples/SNL34m/data/SAND-91-2228_Data/.gitignore b/examples/SNL34m/data/SAND-91-2228_Data/.gitignore new file mode 100644 index 00000000..afed0735 --- /dev/null +++ b/examples/SNL34m/data/SAND-91-2228_Data/.gitignore @@ -0,0 +1 @@ +*.csv diff --git a/examples/dev/airfoils/NACA_0021_AD.dat b/examples/dev/airfoils/NACA_0021_AD.dat new file mode 100644 index 00000000..e4b94c5a --- /dev/null +++ b/examples/dev/airfoils/NACA_0021_AD.dat @@ -0,0 +1,1464 @@ +! ------------ AirfoilInfo v1.01.x Input File ---------------------------------- +! NACA 0018 at Re = 0.01,0.02,0.04,0.08,0.16,0.36,0.70,1,2,5 million +! line +! line +! ------------------------------------------------------------------------------ +DEFAULT InterpOrd - ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] +0.18 RelThickness - ! The non-dimensional thickness of the airfoil (thickness/chord) [only used if UAMod=7] [default=0.2] (-) +1 NonDimArea - ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) +@"NACA_0018_Coords.txt" NumCoords - ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +"NA" BL_file - ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. +10 NumTabs - ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. +! ------------------------------------------------------------------------------ +! data for table 1 +! ------------------------------------------------------------------------------ +0.01 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +8.136711569484852 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-8.136711569484852 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.8163 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-0.1482 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.1545 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +99 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +-1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 +-1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 +-1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 +-1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 +-1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 +-1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 +-1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 +-1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 +-1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 +-1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 +-1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 +-1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 +-1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 +-1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 +-1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 +-1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 +-9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 +-9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 +-8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 +-8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 +-7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 +-7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 +-6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 +-6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 +-5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 +-5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 +-4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 +-4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 +-3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 +-3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 +-2.50000000e+01 -5.77500000e-01 4.05000000e-01 0.00000000e+00 +-2.20000000e+01 -4.17200000e-01 3.29000000e-01 0.00000000e+00 +-2.00000000e+01 -3.11100000e-01 2.82000000e-01 0.00000000e+00 +-1.80000000e+01 -2.07000000e-01 2.38000000e-01 0.00000000e+00 +-1.60000000e+01 -1.05100000e-01 1.96000000e-01 0.00000000e+00 +-1.40000000e+01 -8.50000000e-03 1.58000000e-01 0.00000000e+00 +-1.20000000e+01 7.67000000e-02 1.23000000e-01 0.00000000e+00 +-1.10000000e+01 1.12500000e-01 8.00000000e-02 0.00000000e+00 +-1.00000000e+01 1.42300000e-01 5.74000000e-02 0.00000000e+00 +-9.00000000e+00 1.58400000e-01 5.25000000e-02 0.00000000e+00 +-8.00000000e+00 1.50100000e-01 4.89000000e-02 0.00000000e+00 +-7.00000000e+00 1.18200000e-01 4.63000000e-02 0.00000000e+00 +-6.00000000e+00 8.39000000e-02 4.43000000e-02 0.00000000e+00 +-5.00000000e+00 5.77000000e-02 4.25000000e-02 0.00000000e+00 +-4.00000000e+00 3.68000000e-02 4.10000000e-02 0.00000000e+00 +-3.00000000e+00 2.33000000e-02 3.99000000e-02 0.00000000e+00 +-2.00000000e+00 1.54000000e-02 3.91000000e-02 0.00000000e+00 +-1.00000000e+00 4.50000000e-03 3.87000000e-02 0.00000000e+00 + 0.00000000e+00 0.00000000e+00 3.85000000e-02 0.00000000e+00 + 1.00000000e+00 -4.50000000e-03 3.87000000e-02 0.00000000e+00 + 2.00000000e+00 -1.54000000e-02 3.91000000e-02 0.00000000e+00 + 3.00000000e+00 -2.33000000e-02 3.99000000e-02 0.00000000e+00 + 4.00000000e+00 -3.68000000e-02 4.10000000e-02 0.00000000e+00 + 5.00000000e+00 -5.77000000e-02 4.25000000e-02 0.00000000e+00 + 6.00000000e+00 -8.39000000e-02 4.43000000e-02 0.00000000e+00 + 7.00000000e+00 -1.18200000e-01 4.63000000e-02 0.00000000e+00 + 8.00000000e+00 -1.50100000e-01 4.89000000e-02 0.00000000e+00 + 9.00000000e+00 -1.58400000e-01 5.25000000e-02 0.00000000e+00 + 1.00000000e+01 -1.42300000e-01 5.74000000e-02 0.00000000e+00 + 1.10000000e+01 -1.12500000e-01 8.00000000e-02 0.00000000e+00 + 1.20000000e+01 -7.67000000e-02 1.23000000e-01 0.00000000e+00 + 1.40000000e+01 8.50000000e-03 1.58000000e-01 0.00000000e+00 + 1.60000000e+01 1.05100000e-01 1.96000000e-01 0.00000000e+00 + 1.80000000e+01 2.07000000e-01 2.38000000e-01 0.00000000e+00 + 2.00000000e+01 3.11100000e-01 2.82000000e-01 0.00000000e+00 + 2.20000000e+01 4.17200000e-01 3.29000000e-01 0.00000000e+00 + 2.50000000e+01 5.77500000e-01 4.05000000e-01 0.00000000e+00 + 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 + 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 + 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 + 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 + 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 + 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 + 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 + 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 + 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 + 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 + 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 + 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 + 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 + 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 + 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 + 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 + 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 + 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 + 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 + 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 + 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 + 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 + 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 + 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 + 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 + 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 + 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 + 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 + 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 + 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 + 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +! ------------------------------------------------------------------------------ +! data for table 2 +! ------------------------------------------------------------------------------ +0.02 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +9.154276388714532 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-9.154276388714532 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.1809 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-0.1809 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0286 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +97 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +-1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 +-1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 +-1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 +-1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 +-1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 +-1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 +-1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 +-1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 +-1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 +-1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 +-1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 +-1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 +-1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 +-1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 +-1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 +-1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 +-9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 +-9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 +-8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 +-8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 +-7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 +-7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 +-6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 +-6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 +-5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 +-5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 +-4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 +-4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 +-3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 +-3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 +-2.50000000e+01 -5.79800000e-01 4.05000000e-01 0.00000000e+00 +-2.20000000e+01 -4.19800000e-01 3.29000000e-01 0.00000000e+00 +-2.00000000e+01 -3.15100000e-01 2.82000000e-01 0.00000000e+00 +-1.80000000e+01 -2.12000000e-01 2.38000000e-01 0.00000000e+00 +-1.60000000e+01 -1.11400000e-01 1.96000000e-01 0.00000000e+00 +-1.40000000e+01 -1.72000000e-02 1.58000000e-01 0.00000000e+00 +-1.20000000e+01 6.02000000e-02 1.23000000e-01 0.00000000e+00 +-1.00000000e+01 1.00300000e-01 6.30000000e-02 0.00000000e+00 +-9.00000000e+00 6.82000000e-02 3.96000000e-02 0.00000000e+00 +-8.00000000e+00 -2.14000000e-02 3.76000000e-02 0.00000000e+00 +-7.00000000e+00 -1.16100000e-01 3.58000000e-02 0.00000000e+00 +-6.00000000e+00 -1.58200000e-01 3.39000000e-02 0.00000000e+00 +-5.00000000e+00 -1.78800000e-01 3.23000000e-02 0.00000000e+00 +-4.00000000e+00 -1.78800000e-01 3.10000000e-02 0.00000000e+00 +-3.00000000e+00 -1.55000000e-01 2.99000000e-02 0.00000000e+00 +-2.00000000e+00 -1.13500000e-01 2.92000000e-02 0.00000000e+00 +-1.00000000e+00 -6.07000000e-02 2.88000000e-02 0.00000000e+00 + 0.00000000e+00 0.00000000e+00 2.86000000e-02 0.00000000e+00 + 1.00000000e+00 6.07000000e-02 2.88000000e-02 0.00000000e+00 + 2.00000000e+00 1.13500000e-01 2.92000000e-02 0.00000000e+00 + 3.00000000e+00 1.55000000e-01 2.99000000e-02 0.00000000e+00 + 4.00000000e+00 1.78800000e-01 3.10000000e-02 0.00000000e+00 + 5.00000000e+00 1.78800000e-01 3.23000000e-02 0.00000000e+00 + 6.00000000e+00 1.58200000e-01 3.39000000e-02 0.00000000e+00 + 7.00000000e+00 1.16100000e-01 3.58000000e-02 0.00000000e+00 + 8.00000000e+00 2.14000000e-02 3.76000000e-02 0.00000000e+00 + 9.00000000e+00 -6.82000000e-02 3.96000000e-02 0.00000000e+00 + 1.00000000e+01 -1.00300000e-01 6.30000000e-02 0.00000000e+00 + 1.20000000e+01 -6.02000000e-02 1.23000000e-01 0.00000000e+00 + 1.40000000e+01 1.72000000e-02 1.58000000e-01 0.00000000e+00 + 1.60000000e+01 1.11400000e-01 1.96000000e-01 0.00000000e+00 + 1.80000000e+01 2.12000000e-01 2.38000000e-01 0.00000000e+00 + 2.00000000e+01 3.15100000e-01 2.82000000e-01 0.00000000e+00 + 2.20000000e+01 4.19800000e-01 3.29000000e-01 0.00000000e+00 + 2.50000000e+01 5.79800000e-01 4.05000000e-01 0.00000000e+00 + 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 + 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 + 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 + 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 + 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 + 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 + 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 + 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 + 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 + 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 + 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 + 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 + 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 + 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 + 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 + 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 + 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 + 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 + 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 + 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 + 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 + 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 + 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 + 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 + 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 + 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 + 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 + 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 + 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 + 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 + 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +! ------------------------------------------------------------------------------ +! data for table 3 +! ------------------------------------------------------------------------------ +0.04 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +10.299096322309719 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-10.299096322309719 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.4757 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-0.4757 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0214 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +97 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +-1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 +-1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 +-1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 +-1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 +-1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 +-1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 +-1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 +-1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 +-1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 +-1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 +-1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 +-1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 +-1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 +-1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 +-1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 +-1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 +-9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 +-9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 +-8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 +-8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 +-7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 +-7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 +-6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 +-6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 +-5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 +-5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 +-4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 +-4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 +-3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 +-3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 +-2.50000000e+01 -5.84000000e-01 4.05000000e-01 0.00000000e+00 +-2.20000000e+01 -4.26500000e-01 3.29000000e-01 0.00000000e+00 +-2.00000000e+01 -3.23600000e-01 2.82000000e-01 0.00000000e+00 +-1.80000000e+01 -2.22800000e-01 2.38000000e-01 0.00000000e+00 +-1.60000000e+01 -1.28700000e-01 1.96000000e-01 0.00000000e+00 +-1.40000000e+01 -4.89000000e-02 1.58000000e-01 0.00000000e+00 +-1.20000000e+01 -1.39000000e-02 1.23000000e-01 0.00000000e+00 +-1.00000000e+01 -2.10800000e-01 6.20000000e-02 0.00000000e+00 +-9.00000000e+00 -3.54400000e-01 3.27000000e-02 0.00000000e+00 +-8.00000000e+00 -4.42800000e-01 3.03000000e-02 0.00000000e+00 +-7.00000000e+00 -4.75800000e-01 2.82000000e-02 0.00000000e+00 +-6.00000000e+00 -4.57300000e-01 2.63000000e-02 0.00000000e+00 +-5.00000000e+00 -4.11700000e-01 2.47000000e-02 0.00000000e+00 +-4.00000000e+00 -3.49500000e-01 2.35000000e-02 0.00000000e+00 +-3.00000000e+00 -2.68800000e-01 2.25000000e-02 0.00000000e+00 +-2.00000000e+00 -1.83300000e-01 2.19000000e-02 0.00000000e+00 +-1.00000000e+00 -9.36000000e-02 2.15000000e-02 0.00000000e+00 + 0.00000000e+00 0.00000000e+00 2.14000000e-02 0.00000000e+00 + 1.00000000e+00 9.36000000e-02 2.15000000e-02 0.00000000e+00 + 2.00000000e+00 1.83300000e-01 2.19000000e-02 0.00000000e+00 + 3.00000000e+00 2.68800000e-01 2.25000000e-02 0.00000000e+00 + 4.00000000e+00 3.49500000e-01 2.35000000e-02 0.00000000e+00 + 5.00000000e+00 4.11700000e-01 2.47000000e-02 0.00000000e+00 + 6.00000000e+00 4.57300000e-01 2.63000000e-02 0.00000000e+00 + 7.00000000e+00 4.75800000e-01 2.82000000e-02 0.00000000e+00 + 8.00000000e+00 4.42800000e-01 3.03000000e-02 0.00000000e+00 + 9.00000000e+00 3.54400000e-01 3.27000000e-02 0.00000000e+00 + 1.00000000e+01 2.10800000e-01 6.20000000e-02 0.00000000e+00 + 1.20000000e+01 1.39000000e-02 1.23000000e-01 0.00000000e+00 + 1.40000000e+01 4.89000000e-02 1.58000000e-01 0.00000000e+00 + 1.60000000e+01 1.28700000e-01 1.96000000e-01 0.00000000e+00 + 1.80000000e+01 2.22800000e-01 2.38000000e-01 0.00000000e+00 + 2.00000000e+01 3.23600000e-01 2.82000000e-01 0.00000000e+00 + 2.20000000e+01 4.26500000e-01 3.29000000e-01 0.00000000e+00 + 2.50000000e+01 5.84000000e-01 4.05000000e-01 0.00000000e+00 + 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 + 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 + 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 + 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 + 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 + 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 + 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 + 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 + 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 + 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 + 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 + 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 + 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 + 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 + 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 + 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 + 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 + 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 + 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 + 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 + 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 + 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 + 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 + 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 + 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 + 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 + 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 + 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 + 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 + 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 + 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +! ------------------------------------------------------------------------------ +! data for table 4 +! ------------------------------------------------------------------------------ +0.08 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +11.587085702041861 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-11.587085702041861 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.6566 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-0.6566 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0162 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +99 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +-1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 +-1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 +-1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 +-1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 +-1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 +-1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 +-1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 +-1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 +-1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 +-1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 +-1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 +-1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 +-1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 +-1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 +-1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 +-1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 +-9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 +-9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 +-8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 +-8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 +-7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 +-7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 +-6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 +-6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 +-5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 +-5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 +-4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 +-4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 +-3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 +-3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 +-2.50000000e+01 -5.96300000e-01 4.05000000e-01 0.00000000e+00 +-2.20000000e+01 -4.43000000e-01 3.29000000e-01 0.00000000e+00 +-2.00000000e+01 -3.47200000e-01 2.82000000e-01 0.00000000e+00 +-1.80000000e+01 -2.60300000e-01 2.38000000e-01 0.00000000e+00 +-1.60000000e+01 -2.02700000e-01 1.96000000e-01 0.00000000e+00 +-1.40000000e+01 -2.25600000e-01 1.58000000e-01 0.00000000e+00 +-1.20000000e+01 -4.40800000e-01 8.00000000e-02 0.00000000e+00 +-1.10000000e+01 -5.53100000e-01 3.15000000e-02 0.00000000e+00 +-1.00000000e+01 -6.24800000e-01 2.88000000e-02 0.00000000e+00 +-9.00000000e+00 -6.60600000e-01 2.64000000e-02 0.00000000e+00 +-8.00000000e+00 -6.58900000e-01 2.42000000e-02 0.00000000e+00 +-7.00000000e+00 -6.22400000e-01 2.23000000e-02 0.00000000e+00 +-6.00000000e+00 -5.61500000e-01 2.06000000e-02 0.00000000e+00 +-5.00000000e+00 -4.75300000e-01 1.92000000e-02 0.00000000e+00 +-4.00000000e+00 -3.88000000e-01 1.81000000e-02 0.00000000e+00 +-3.00000000e+00 -2.92400000e-01 1.72000000e-02 0.00000000e+00 +-2.00000000e+00 -1.93500000e-01 1.67000000e-02 0.00000000e+00 +-1.00000000e+00 -8.89000000e-02 1.63000000e-02 0.00000000e+00 + 0.00000000e+00 0.00000000e+00 1.62000000e-02 0.00000000e+00 + 1.00000000e+00 8.89000000e-02 1.63000000e-02 0.00000000e+00 + 2.00000000e+00 1.93500000e-01 1.67000000e-02 0.00000000e+00 + 3.00000000e+00 2.92400000e-01 1.72000000e-02 0.00000000e+00 + 4.00000000e+00 3.88000000e-01 1.81000000e-02 0.00000000e+00 + 5.00000000e+00 4.75300000e-01 1.92000000e-02 0.00000000e+00 + 6.00000000e+00 5.61500000e-01 2.06000000e-02 0.00000000e+00 + 7.00000000e+00 6.22400000e-01 2.23000000e-02 0.00000000e+00 + 8.00000000e+00 6.58900000e-01 2.42000000e-02 0.00000000e+00 + 9.00000000e+00 6.60600000e-01 2.64000000e-02 0.00000000e+00 + 1.00000000e+01 6.24800000e-01 2.88000000e-02 0.00000000e+00 + 1.10000000e+01 5.53100000e-01 3.15000000e-02 0.00000000e+00 + 1.20000000e+01 4.40800000e-01 8.00000000e-02 0.00000000e+00 + 1.40000000e+01 2.25600000e-01 1.58000000e-01 0.00000000e+00 + 1.60000000e+01 2.02700000e-01 1.96000000e-01 0.00000000e+00 + 1.80000000e+01 2.60300000e-01 2.38000000e-01 0.00000000e+00 + 2.00000000e+01 3.47200000e-01 2.82000000e-01 0.00000000e+00 + 2.20000000e+01 4.43000000e-01 3.29000000e-01 0.00000000e+00 + 2.50000000e+01 5.96300000e-01 4.05000000e-01 0.00000000e+00 + 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 + 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 + 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 + 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 + 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 + 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 + 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 + 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 + 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 + 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 + 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 + 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 + 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 + 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 + 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 + 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 + 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 + 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 + 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 + 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 + 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 + 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 + 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 + 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 + 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 + 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 + 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 + 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 + 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 + 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 + 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +! ------------------------------------------------------------------------------ +! data for table 5 +! ------------------------------------------------------------------------------ +0.16 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +13.036149081898586 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-13.036149081898586 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.787 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-0.787 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0128 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +101 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +-1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 +-1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 +-1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 +-1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 +-1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 +-1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 +-1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 +-1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 +-1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 +-1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 +-1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 +-1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 +-1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 +-1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 +-1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 +-1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 +-9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 +-9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 +-8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 +-8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 +-7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 +-7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 +-6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 +-6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 +-5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 +-5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 +-4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 +-4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 +-3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 +-3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 +-2.50000000e+01 -6.32100000e-01 4.05000000e-01 0.00000000e+00 +-2.20000000e+01 -5.02600000e-01 3.29000000e-01 0.00000000e+00 +-2.00000000e+01 -4.38200000e-01 2.82000000e-01 0.00000000e+00 +-1.80000000e+01 -4.20200000e-01 2.38000000e-01 0.00000000e+00 +-1.60000000e+01 -4.89600000e-01 1.96000000e-01 0.00000000e+00 +-1.40000000e+01 -6.23700000e-01 1.58000000e-01 0.00000000e+00 +-1.30000000e+01 -6.92300000e-01 7.70000000e-02 0.00000000e+00 +-1.20000000e+01 -7.48800000e-01 2.88000000e-02 0.00000000e+00 +-1.10000000e+01 -7.85200000e-01 2.62000000e-02 0.00000000e+00 +-1.00000000e+01 -7.94900000e-01 2.38000000e-02 0.00000000e+00 +-9.00000000e+00 -7.78100000e-01 2.17000000e-02 0.00000000e+00 +-8.00000000e+00 -7.37300000e-01 1.98000000e-02 0.00000000e+00 +-7.00000000e+00 -6.72400000e-01 1.81000000e-02 0.00000000e+00 +-6.00000000e+00 -5.96000000e-01 1.66000000e-02 0.00000000e+00 +-5.00000000e+00 -5.06800000e-01 1.53000000e-02 0.00000000e+00 +-4.00000000e+00 -4.11400000e-01 1.44000000e-02 0.00000000e+00 +-3.00000000e+00 -3.08800000e-01 1.37000000e-02 0.00000000e+00 +-2.00000000e+00 -2.20000000e-01 1.31000000e-02 0.00000000e+00 +-1.00000000e+00 -1.10000000e-01 1.29000000e-02 0.00000000e+00 + 0.00000000e+00 0.00000000e+00 1.28000000e-02 0.00000000e+00 + 1.00000000e+00 1.10000000e-01 1.29000000e-02 0.00000000e+00 + 2.00000000e+00 2.20000000e-01 1.31000000e-02 0.00000000e+00 + 3.00000000e+00 3.08800000e-01 1.37000000e-02 0.00000000e+00 + 4.00000000e+00 4.11400000e-01 1.44000000e-02 0.00000000e+00 + 5.00000000e+00 5.06800000e-01 1.53000000e-02 0.00000000e+00 + 6.00000000e+00 5.96000000e-01 1.66000000e-02 0.00000000e+00 + 7.00000000e+00 6.72400000e-01 1.81000000e-02 0.00000000e+00 + 8.00000000e+00 7.37300000e-01 1.98000000e-02 0.00000000e+00 + 9.00000000e+00 7.78100000e-01 2.17000000e-02 0.00000000e+00 + 1.00000000e+01 7.94900000e-01 2.38000000e-02 0.00000000e+00 + 1.10000000e+01 7.85200000e-01 2.62000000e-02 0.00000000e+00 + 1.20000000e+01 7.48800000e-01 2.88000000e-02 0.00000000e+00 + 1.30000000e+01 6.92300000e-01 7.70000000e-02 0.00000000e+00 + 1.40000000e+01 6.23700000e-01 1.58000000e-01 0.00000000e+00 + 1.60000000e+01 4.89600000e-01 1.96000000e-01 0.00000000e+00 + 1.80000000e+01 4.20200000e-01 2.38000000e-01 0.00000000e+00 + 2.00000000e+01 4.38200000e-01 2.82000000e-01 0.00000000e+00 + 2.20000000e+01 5.02600000e-01 3.29000000e-01 0.00000000e+00 + 2.50000000e+01 6.32100000e-01 4.05000000e-01 0.00000000e+00 + 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 + 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 + 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 + 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 + 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 + 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 + 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 + 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 + 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 + 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 + 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 + 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 + 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 + 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 + 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 + 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 + 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 + 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 + 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 + 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 + 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 + 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 + 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 + 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 + 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 + 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 + 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 + 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 + 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 + 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 + 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +! ------------------------------------------------------------------------------ +! data for table 6 +! ------------------------------------------------------------------------------ +0.36 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +14.963057557300898 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-14.963057557300898 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.9125 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-0.9125 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0101 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +101 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +-1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 +-1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 +-1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 +-1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 +-1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 +-1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 +-1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 +-1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 +-1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 +-1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 +-1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 +-1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 +-1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 +-1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 +-1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 +-1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 +-9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 +-9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 +-8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 +-8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 +-7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 +-7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 +-6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 +-6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 +-5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 +-5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 +-4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 +-4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 +-3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 +-3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 +-2.50000000e+01 -7.72400000e-01 4.05000000e-01 0.00000000e+00 +-2.20000000e+01 -7.05000000e-01 3.29000000e-01 0.00000000e+00 +-2.00000000e+01 -6.99700000e-01 2.82000000e-01 0.00000000e+00 +-1.80000000e+01 -7.31900000e-01 2.38000000e-01 0.00000000e+00 +-1.60000000e+01 -8.00700000e-01 1.96000000e-01 0.00000000e+00 +-1.40000000e+01 -8.80300000e-01 9.40000000e-02 0.00000000e+00 +-1.30000000e+01 -9.10400000e-01 2.59000000e-02 0.00000000e+00 +-1.20000000e+01 -9.27900000e-01 2.35000000e-02 0.00000000e+00 +-1.10000000e+01 -9.24900000e-01 2.13000000e-02 0.00000000e+00 +-1.00000000e+01 -8.98300000e-01 1.94000000e-02 0.00000000e+00 +-9.00000000e+00 -8.52600000e-01 1.76000000e-02 0.00000000e+00 +-8.00000000e+00 -7.87900000e-01 1.59000000e-02 0.00000000e+00 +-7.00000000e+00 -7.10000000e-01 1.45000000e-02 0.00000000e+00 +-6.00000000e+00 -6.22800000e-01 1.32000000e-02 0.00000000e+00 +-5.00000000e+00 -5.24000000e-01 1.21000000e-02 0.00000000e+00 +-4.00000000e+00 -4.40000000e-01 1.12000000e-02 0.00000000e+00 +-3.00000000e+00 -3.30000000e-01 1.07000000e-02 0.00000000e+00 +-2.00000000e+00 -2.20000000e-01 1.04000000e-02 0.00000000e+00 +-1.00000000e+00 -1.10000000e-01 1.02000000e-02 0.00000000e+00 + 0.00000000e+00 0.00000000e+00 1.01000000e-02 0.00000000e+00 + 1.00000000e+00 1.10000000e-01 1.02000000e-02 0.00000000e+00 + 2.00000000e+00 2.20000000e-01 1.04000000e-02 0.00000000e+00 + 3.00000000e+00 3.30000000e-01 1.07000000e-02 0.00000000e+00 + 4.00000000e+00 4.40000000e-01 1.12000000e-02 0.00000000e+00 + 5.00000000e+00 5.24000000e-01 1.21000000e-02 0.00000000e+00 + 6.00000000e+00 6.22800000e-01 1.32000000e-02 0.00000000e+00 + 7.00000000e+00 7.10000000e-01 1.45000000e-02 0.00000000e+00 + 8.00000000e+00 7.87900000e-01 1.59000000e-02 0.00000000e+00 + 9.00000000e+00 8.52600000e-01 1.76000000e-02 0.00000000e+00 + 1.00000000e+01 8.98300000e-01 1.94000000e-02 0.00000000e+00 + 1.10000000e+01 9.24900000e-01 2.13000000e-02 0.00000000e+00 + 1.20000000e+01 9.27900000e-01 2.35000000e-02 0.00000000e+00 + 1.30000000e+01 9.10400000e-01 2.59000000e-02 0.00000000e+00 + 1.40000000e+01 8.80300000e-01 9.40000000e-02 0.00000000e+00 + 1.60000000e+01 8.00700000e-01 1.96000000e-01 0.00000000e+00 + 1.80000000e+01 7.31900000e-01 2.38000000e-01 0.00000000e+00 + 2.00000000e+01 6.99700000e-01 2.82000000e-01 0.00000000e+00 + 2.20000000e+01 7.05000000e-01 3.29000000e-01 0.00000000e+00 + 2.50000000e+01 7.72400000e-01 4.05000000e-01 0.00000000e+00 + 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 + 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 + 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 + 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 + 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 + 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 + 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 + 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 + 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 + 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 + 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 + 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 + 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 + 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 + 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 + 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 + 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 + 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 + 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 + 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 + 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 + 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 + 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 + 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 + 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 + 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 + 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 + 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 + 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 + 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 + 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +! ------------------------------------------------------------------------------ +! data for table 7 +! ------------------------------------------------------------------------------ +0.7 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +16.7538872411828 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-16.7538872411828 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.0075 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.0075 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0085 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +103 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +-1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 +-1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 +-1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 +-1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 +-1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 +-1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 +-1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 +-1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 +-1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 +-1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 +-1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 +-1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 +-1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 +-1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 +-1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 +-1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 +-9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 +-9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 +-8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 +-8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 +-7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 +-7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 +-6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 +-6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 +-5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 +-5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 +-4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 +-4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 +-3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 +-3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 +-2.50000000e+01 -9.32600000e-01 4.05000000e-01 0.00000000e+00 +-2.20000000e+01 -8.86700000e-01 3.29000000e-01 0.00000000e+00 +-2.00000000e+01 -8.87700000e-01 2.82000000e-01 0.00000000e+00 +-1.80000000e+01 -9.15000000e-01 2.38000000e-01 0.00000000e+00 +-1.60000000e+01 -9.64800000e-01 1.96000000e-01 0.00000000e+00 +-1.50000000e+01 -9.93800000e-01 1.02000000e-01 0.00000000e+00 +-1.40000000e+01 -1.01750000e+00 2.45000000e-02 0.00000000e+00 +-1.30000000e+01 -1.02890000e+00 2.23000000e-02 0.00000000e+00 +-1.20000000e+01 -1.02450000e+00 2.02000000e-02 0.00000000e+00 +-1.10000000e+01 -9.97300000e-01 1.83000000e-02 0.00000000e+00 +-1.00000000e+01 -9.54100000e-01 1.66000000e-02 0.00000000e+00 +-9.00000000e+00 -8.90400000e-01 1.50000000e-02 0.00000000e+00 +-8.00000000e+00 -8.15600000e-01 1.36000000e-02 0.00000000e+00 +-7.00000000e+00 -7.29100000e-01 1.23000000e-02 0.00000000e+00 +-6.00000000e+00 -6.32800000e-01 1.12000000e-02 0.00000000e+00 +-5.00000000e+00 -5.50000000e-01 1.02000000e-02 0.00000000e+00 +-4.00000000e+00 -4.40000000e-01 9.60000000e-03 0.00000000e+00 +-3.00000000e+00 -3.30000000e-01 9.10000000e-03 0.00000000e+00 +-2.00000000e+00 -2.20000000e-01 8.80000000e-03 0.00000000e+00 +-1.00000000e+00 -1.10000000e-01 8.70000000e-03 0.00000000e+00 + 0.00000000e+00 0.00000000e+00 8.50000000e-03 0.00000000e+00 + 1.00000000e+00 1.10000000e-01 8.70000000e-03 0.00000000e+00 + 2.00000000e+00 2.20000000e-01 8.80000000e-03 0.00000000e+00 + 3.00000000e+00 3.30000000e-01 9.10000000e-03 0.00000000e+00 + 4.00000000e+00 4.40000000e-01 9.60000000e-03 0.00000000e+00 + 5.00000000e+00 5.50000000e-01 1.02000000e-02 0.00000000e+00 + 6.00000000e+00 6.32800000e-01 1.12000000e-02 0.00000000e+00 + 7.00000000e+00 7.29100000e-01 1.23000000e-02 0.00000000e+00 + 8.00000000e+00 8.15600000e-01 1.36000000e-02 0.00000000e+00 + 9.00000000e+00 8.90400000e-01 1.50000000e-02 0.00000000e+00 + 1.00000000e+01 9.54100000e-01 1.66000000e-02 0.00000000e+00 + 1.10000000e+01 9.97300000e-01 1.83000000e-02 0.00000000e+00 + 1.20000000e+01 1.02450000e+00 2.02000000e-02 0.00000000e+00 + 1.30000000e+01 1.02890000e+00 2.23000000e-02 0.00000000e+00 + 1.40000000e+01 1.01750000e+00 2.45000000e-02 0.00000000e+00 + 1.50000000e+01 9.93800000e-01 1.02000000e-01 0.00000000e+00 + 1.60000000e+01 9.64800000e-01 1.96000000e-01 0.00000000e+00 + 1.80000000e+01 9.15000000e-01 2.38000000e-01 0.00000000e+00 + 2.00000000e+01 8.87700000e-01 2.82000000e-01 0.00000000e+00 + 2.20000000e+01 8.86700000e-01 3.29000000e-01 0.00000000e+00 + 2.50000000e+01 9.32600000e-01 4.05000000e-01 0.00000000e+00 + 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 + 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 + 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 + 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 + 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 + 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 + 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 + 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 + 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 + 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 + 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 + 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 + 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 + 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 + 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 + 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 + 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 + 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 + 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 + 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 + 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 + 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 + 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 + 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 + 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 + 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 + 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 + 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 + 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 + 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 + 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +! ------------------------------------------------------------------------------ +! data for table 8 +! ------------------------------------------------------------------------------ +1.0 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +17.801185316865297 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-17.801185316865297 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.0573 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.0573 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0082 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +103 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +-1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 +-1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 +-1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 +-1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 +-1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 +-1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 +-1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 +-1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 +-1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 +-1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 +-1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 +-1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 +-1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 +-1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 +-1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 +-1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 +-9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 +-9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 +-8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 +-8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 +-7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 +-7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 +-6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 +-6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 +-5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 +-5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 +-4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 +-4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 +-3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 +-3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 +-2.50000000e+01 -1.01070000e+00 4.05000000e-01 0.00000000e+00 +-2.20000000e+01 -9.69600000e-01 3.29000000e-01 0.00000000e+00 +-2.00000000e+01 -9.70700000e-01 2.82000000e-01 0.00000000e+00 +-1.80000000e+01 -9.95900000e-01 2.38000000e-01 0.00000000e+00 +-1.60000000e+01 -1.04020000e+00 1.08000000e-01 0.00000000e+00 +-1.50000000e+01 -1.06240000e+00 2.51000000e-02 0.00000000e+00 +-1.40000000e+01 -1.07930000e+00 2.27000000e-02 0.00000000e+00 +-1.30000000e+01 -1.08040000e+00 2.06000000e-02 0.00000000e+00 +-1.20000000e+01 -1.06640000e+00 1.87000000e-02 0.00000000e+00 +-1.10000000e+01 -1.02840000e+00 1.70000000e-02 0.00000000e+00 +-1.00000000e+01 -9.75100000e-01 1.54000000e-02 0.00000000e+00 +-9.00000000e+00 -9.06700000e-01 1.39000000e-02 0.00000000e+00 +-8.00000000e+00 -8.25600000e-01 1.26000000e-02 0.00000000e+00 +-7.00000000e+00 -7.36200000e-01 1.15000000e-02 0.00000000e+00 +-6.00000000e+00 -6.60000000e-01 1.02000000e-02 0.00000000e+00 +-5.00000000e+00 -5.50000000e-01 9.50000000e-03 0.00000000e+00 +-4.00000000e+00 -4.40000000e-01 8.90000000e-03 0.00000000e+00 +-3.00000000e+00 -3.30000000e-01 8.60000000e-03 0.00000000e+00 +-2.00000000e+00 -2.20000000e-01 8.30000000e-03 0.00000000e+00 +-1.00000000e+00 -1.10000000e-01 8.20000000e-03 0.00000000e+00 + 0.00000000e+00 0.00000000e+00 8.20000000e-03 0.00000000e+00 + 1.00000000e+00 1.10000000e-01 8.20000000e-03 0.00000000e+00 + 2.00000000e+00 2.20000000e-01 8.30000000e-03 0.00000000e+00 + 3.00000000e+00 3.30000000e-01 8.60000000e-03 0.00000000e+00 + 4.00000000e+00 4.40000000e-01 8.90000000e-03 0.00000000e+00 + 5.00000000e+00 5.50000000e-01 9.50000000e-03 0.00000000e+00 + 6.00000000e+00 6.60000000e-01 1.02000000e-02 0.00000000e+00 + 7.00000000e+00 7.36200000e-01 1.15000000e-02 0.00000000e+00 + 8.00000000e+00 8.25600000e-01 1.26000000e-02 0.00000000e+00 + 9.00000000e+00 9.06700000e-01 1.39000000e-02 0.00000000e+00 + 1.00000000e+01 9.75100000e-01 1.54000000e-02 0.00000000e+00 + 1.10000000e+01 1.02840000e+00 1.70000000e-02 0.00000000e+00 + 1.20000000e+01 1.06640000e+00 1.87000000e-02 0.00000000e+00 + 1.30000000e+01 1.08040000e+00 2.06000000e-02 0.00000000e+00 + 1.40000000e+01 1.07930000e+00 2.27000000e-02 0.00000000e+00 + 1.50000000e+01 1.06240000e+00 2.51000000e-02 0.00000000e+00 + 1.60000000e+01 1.04020000e+00 1.08000000e-01 0.00000000e+00 + 1.80000000e+01 9.95900000e-01 2.38000000e-01 0.00000000e+00 + 2.00000000e+01 9.70700000e-01 2.82000000e-01 0.00000000e+00 + 2.20000000e+01 9.69600000e-01 3.29000000e-01 0.00000000e+00 + 2.50000000e+01 1.01070000e+00 4.05000000e-01 0.00000000e+00 + 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 + 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 + 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 + 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 + 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 + 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 + 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 + 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 + 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 + 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 + 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 + 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 + 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 + 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 + 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 + 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 + 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 + 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 + 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 + 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 + 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 + 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 + 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 + 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 + 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 + 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 + 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 + 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 + 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 + 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 + 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +! ------------------------------------------------------------------------------ +! data for table 9 +! ------------------------------------------------------------------------------ +2.0 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +20.027374578257152 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-20.027374578257152 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.151 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.151 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0077 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +105 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +-1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 +-1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 +-1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 +-1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 +-1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 +-1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 +-1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 +-1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 +-1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 +-1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 +-1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 +-1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 +-1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 +-1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 +-1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 +-1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 +-9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 +-9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 +-8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 +-8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 +-7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 +-7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 +-6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 +-6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 +-5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 +-5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 +-4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 +-4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 +-3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 +-3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 +-2.50000000e+01 -1.14680000e+00 4.05000000e-01 0.00000000e+00 +-2.20000000e+01 -1.11270000e+00 3.29000000e-01 0.00000000e+00 +-2.00000000e+01 -1.11720000e+00 2.82000000e-01 0.00000000e+00 +-1.80000000e+01 -1.13830000e+00 2.38000000e-01 0.00000000e+00 +-1.70000000e+01 -1.15500000e+00 1.20000000e-01 0.00000000e+00 +-1.60000000e+01 -1.16950000e+00 2.40000000e-02 0.00000000e+00 +-1.50000000e+01 -1.18130000e+00 2.18000000e-02 0.00000000e+00 +-1.40000000e+01 -1.18130000e+00 1.97000000e-02 0.00000000e+00 +-1.30000000e+01 -1.16620000e+00 1.79000000e-02 0.00000000e+00 +-1.20000000e+01 -1.12960000e+00 1.63000000e-02 0.00000000e+00 +-1.10000000e+01 -1.07720000e+00 1.48000000e-02 0.00000000e+00 +-1.00000000e+01 -1.01110000e+00 1.34000000e-02 0.00000000e+00 +-9.00000000e+00 -9.31400000e-01 1.22000000e-02 0.00000000e+00 +-8.00000000e+00 -8.43900000e-01 1.11000000e-02 0.00000000e+00 +-7.00000000e+00 -7.44900000e-01 1.01000000e-02 0.00000000e+00 +-6.00000000e+00 -6.60000000e-01 9.30000000e-03 0.00000000e+00 +-5.00000000e+00 -5.50000000e-01 8.70000000e-03 0.00000000e+00 +-4.00000000e+00 -4.40000000e-01 8.40000000e-03 0.00000000e+00 +-3.00000000e+00 -3.30000000e-01 8.00000000e-03 0.00000000e+00 +-2.00000000e+00 -2.20000000e-01 7.80000000e-03 0.00000000e+00 +-1.00000000e+00 -1.10000000e-01 7.70000000e-03 0.00000000e+00 + 0.00000000e+00 0.00000000e+00 7.70000000e-03 0.00000000e+00 + 1.00000000e+00 1.10000000e-01 7.70000000e-03 0.00000000e+00 + 2.00000000e+00 2.20000000e-01 7.80000000e-03 0.00000000e+00 + 3.00000000e+00 3.30000000e-01 8.00000000e-03 0.00000000e+00 + 4.00000000e+00 4.40000000e-01 8.40000000e-03 0.00000000e+00 + 5.00000000e+00 5.50000000e-01 8.70000000e-03 0.00000000e+00 + 6.00000000e+00 6.60000000e-01 9.30000000e-03 0.00000000e+00 + 7.00000000e+00 7.44900000e-01 1.01000000e-02 0.00000000e+00 + 8.00000000e+00 8.43900000e-01 1.11000000e-02 0.00000000e+00 + 9.00000000e+00 9.31400000e-01 1.22000000e-02 0.00000000e+00 + 1.00000000e+01 1.01110000e+00 1.34000000e-02 0.00000000e+00 + 1.10000000e+01 1.07720000e+00 1.48000000e-02 0.00000000e+00 + 1.20000000e+01 1.12960000e+00 1.63000000e-02 0.00000000e+00 + 1.30000000e+01 1.16620000e+00 1.79000000e-02 0.00000000e+00 + 1.40000000e+01 1.18130000e+00 1.97000000e-02 0.00000000e+00 + 1.50000000e+01 1.18130000e+00 2.18000000e-02 0.00000000e+00 + 1.60000000e+01 1.16950000e+00 2.40000000e-02 0.00000000e+00 + 1.70000000e+01 1.15500000e+00 1.20000000e-01 0.00000000e+00 + 1.80000000e+01 1.13830000e+00 2.38000000e-01 0.00000000e+00 + 2.00000000e+01 1.11720000e+00 2.82000000e-01 0.00000000e+00 + 2.20000000e+01 1.11270000e+00 3.29000000e-01 0.00000000e+00 + 2.50000000e+01 1.14680000e+00 4.05000000e-01 0.00000000e+00 + 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 + 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 + 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 + 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 + 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 + 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 + 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 + 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 + 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 + 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 + 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 + 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 + 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 + 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 + 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 + 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 + 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 + 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 + 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 + 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 + 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 + 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 + 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 + 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 + 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 + 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 + 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 + 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 + 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 + 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 + 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +! ------------------------------------------------------------------------------ +! data for table 10 +! ------------------------------------------------------------------------------ +5.0 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +23.403123375221707 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-23.403123375221707 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.2617 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.2617 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0073 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +107 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +-1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 +-1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 +-1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 +-1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 +-1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 +-1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 +-1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 +-1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 +-1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 +-1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 +-1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 +-1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 +-1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 +-1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 +-1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 +-1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 +-9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 +-9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 +-8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 +-8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 +-7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 +-7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 +-6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 +-6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 +-5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 +-5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 +-4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 +-4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 +-3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 +-3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 +-2.50000000e+01 -1.29250000e+00 4.05000000e-01 0.00000000e+00 +-2.20000000e+01 -1.27140000e+00 3.29000000e-01 0.00000000e+00 +-2.00000000e+01 -1.27680000e+00 2.82000000e-01 0.00000000e+00 +-1.90000000e+01 -1.28530000e+00 1.40000000e-01 0.00000000e+00 +-1.80000000e+01 -1.29600000e+00 2.44000000e-02 0.00000000e+00 +-1.70000000e+01 -1.30380000e+00 2.23000000e-02 0.00000000e+00 +-1.60000000e+01 -1.30670000e+00 2.03000000e-02 0.00000000e+00 +-1.50000000e+01 -1.30040000e+00 1.85000000e-02 0.00000000e+00 +-1.40000000e+01 -1.28080000e+00 1.68000000e-02 0.00000000e+00 +-1.30000000e+01 -1.24300000e+00 1.53000000e-02 0.00000000e+00 +-1.20000000e+01 -1.18840000e+00 1.40000000e-02 0.00000000e+00 +-1.10000000e+01 -1.12110000e+00 1.28000000e-02 0.00000000e+00 +-1.00000000e+01 -1.04040000e+00 1.17000000e-02 0.00000000e+00 +-9.00000000e+00 -9.52500000e-01 1.08000000e-02 0.00000000e+00 +-8.00000000e+00 -8.53800000e-01 1.00000000e-02 0.00000000e+00 +-7.00000000e+00 -7.70000000e-01 9.30000000e-03 0.00000000e+00 +-6.00000000e+00 -6.60000000e-01 8.70000000e-03 0.00000000e+00 +-5.00000000e+00 -5.50000000e-01 8.30000000e-03 0.00000000e+00 +-4.00000000e+00 -4.40000000e-01 7.90000000e-03 0.00000000e+00 +-3.00000000e+00 -3.30000000e-01 7.70000000e-03 0.00000000e+00 +-2.00000000e+00 -2.20000000e-01 7.50000000e-03 0.00000000e+00 +-1.00000000e+00 -1.10000000e-01 7.30000000e-03 0.00000000e+00 + 0.00000000e+00 0.00000000e+00 7.30000000e-03 0.00000000e+00 + 1.00000000e+00 1.10000000e-01 7.30000000e-03 0.00000000e+00 + 2.00000000e+00 2.20000000e-01 7.50000000e-03 0.00000000e+00 + 3.00000000e+00 3.30000000e-01 7.70000000e-03 0.00000000e+00 + 4.00000000e+00 4.40000000e-01 7.90000000e-03 0.00000000e+00 + 5.00000000e+00 5.50000000e-01 8.30000000e-03 0.00000000e+00 + 6.00000000e+00 6.60000000e-01 8.70000000e-03 0.00000000e+00 + 7.00000000e+00 7.70000000e-01 9.30000000e-03 0.00000000e+00 + 8.00000000e+00 8.53800000e-01 1.00000000e-02 0.00000000e+00 + 9.00000000e+00 9.52500000e-01 1.08000000e-02 0.00000000e+00 + 1.00000000e+01 1.04040000e+00 1.17000000e-02 0.00000000e+00 + 1.10000000e+01 1.12110000e+00 1.28000000e-02 0.00000000e+00 + 1.20000000e+01 1.18840000e+00 1.40000000e-02 0.00000000e+00 + 1.30000000e+01 1.24300000e+00 1.53000000e-02 0.00000000e+00 + 1.40000000e+01 1.28080000e+00 1.68000000e-02 0.00000000e+00 + 1.50000000e+01 1.30040000e+00 1.85000000e-02 0.00000000e+00 + 1.60000000e+01 1.30670000e+00 2.03000000e-02 0.00000000e+00 + 1.70000000e+01 1.30380000e+00 2.23000000e-02 0.00000000e+00 + 1.80000000e+01 1.29600000e+00 2.44000000e-02 0.00000000e+00 + 1.90000000e+01 1.28530000e+00 1.40000000e-01 0.00000000e+00 + 2.00000000e+01 1.27680000e+00 2.82000000e-01 0.00000000e+00 + 2.20000000e+01 1.27140000e+00 3.29000000e-01 0.00000000e+00 + 2.50000000e+01 1.29250000e+00 4.05000000e-01 0.00000000e+00 + 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 + 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 + 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 + 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 + 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 + 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 + 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 + 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 + 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 + 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 + 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 + 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 + 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 + 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 + 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 + 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 + 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 + 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 + 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 + 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 + 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 + 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 + 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 + 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 + 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 + 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 + 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 + 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 + 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 + 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 + 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 + diff --git a/examples/dev/airfoils/NACA_0021_DMS.dat b/examples/dev/airfoils/NACA_0021_DMS.dat new file mode 100644 index 00000000..086fb2f0 --- /dev/null +++ b/examples/dev/airfoils/NACA_0021_DMS.dat @@ -0,0 +1,1211 @@ +Title: NACA0021 +Thickness to Chord Ratio: 0.21 +Zero Lift AOA (deg): 0.0 +Reverse Camber Direction: 0 + +Reynolds Number: 1e4 +BV Dyn. Stall Model - Positive Stall AOA (deg): 1.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -1.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 5.73 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1 +AOA (deg) CL CD Cm25 +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -0.453900000000000 0.405000000000000 0 +-22 -0.300200000000000 0.329000000000000 0 +-20 -0.200600000000000 0.282000000000000 0 +-18 -0.103500000000000 0.238000000000000 0 +-16 -0.0123000000000000 0.196000000000000 0 +-14 0.0658000000000000 0.158000000000000 0 +-12 0.127600000000000 0.123000000000000 0 +-10 0.158100000000000 0.0750000000000000 0 +-9 0.158100000000000 0.0575000000000000 0 +-8 0.147500000000000 0.0538000000000000 0 +-7 0.140000000000000 0.0507000000000000 0 +-6 0.124000000000000 0.0480000000000000 0 +-5 0.115600000000000 0.0459000000000000 0 +-4 0.0995000000000000 0.0441000000000000 0 +-3 0.0854000000000000 0.0429000000000000 0 +-2 0.0631000000000000 0.0420000000000000 0 +-1 0.0320000000000000 0.0414000000000000 0 +0 0 0.0413000000000000 0 +1 -0.0320000000000000 0.0414000000000000 0 +2 -0.0631000000000000 0.0420000000000000 0 +3 -0.0854000000000000 0.0429000000000000 0 +4 -0.0995000000000000 0.0441000000000000 0 +5 -0.115600000000000 0.0459000000000000 0 +6 -0.124000000000000 0.0480000000000000 0 +7 -0.140000000000000 0.0507000000000000 0 +8 -0.147500000000000 0.0538000000000000 0 +9 -0.158100000000000 0.0575000000000000 0 +10 -0.158100000000000 0.0750000000000000 0 +12 -0.127600000000000 0.123000000000000 0 +14 -0.0658000000000000 0.158000000000000 0 +16 0.0123000000000000 0.196000000000000 0 +18 0.103500000000000 0.238000000000000 0 +20 0.200600000000000 0.282000000000000 0 +22 0.300200000000000 0.329000000000000 0 +25 0.453900000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 + +Reynolds Number: 2e4 +BV Dyn. Stall Model - Positive Stall AOA (deg): 1.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -1.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 5.73 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1 +AOA (deg) CL CD Cm25 +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -0.461800000000000 0.405000000000000 0 +-22 -0.310300000000000 0.329000000000000 0 +-20 -0.212400000000000 0.282000000000000 0 +-18 -0.118000000000000 0.238000000000000 0 +-16 -0.0331000000000000 0.196000000000000 0 +-14 0.0362000000000000 0.158000000000000 0 +-12 0.0713000000000000 0.123000000000000 0 +-10 0.0506000000000000 0.0700000000000000 0 +-9 0.0190000000000000 0.0435000000000000 0 +-8 -0.0120000000000000 0.0407000000000000 0 +-7 -0.0266000000000000 0.0382000000000000 0 +-6 -0.0475000000000000 0.0362000000000000 0 +-5 -0.0505000000000000 0.0345000000000000 0 +-4 -0.0619000000000000 0.0332000000000000 0 +-3 -0.0472000000000000 0.0321000000000000 0 +-2 -0.0393000000000000 0.0314000000000000 0 +-1 -0.0243000000000000 0.0310000000000000 0 +0 0 0.0309000000000000 0 +1 0.0243000000000000 0.0310000000000000 0 +2 0.0393000000000000 0.0314000000000000 0 +3 0.0472000000000000 0.0321000000000000 0 +4 0.0619000000000000 0.0332000000000000 0 +5 0.0505000000000000 0.0345000000000000 0 +6 0.0475000000000000 0.0362000000000000 0 +7 0.0266000000000000 0.0382000000000000 0 +8 0.0120000000000000 0.0407000000000000 0 +9 -0.0190000000000000 0.0435000000000000 0 +10 -0.0506000000000000 0.0700000000000000 0 +12 -0.0713000000000000 0.123000000000000 0 +14 -0.0362000000000000 0.158000000000000 0 +16 0.0331000000000000 0.196000000000000 0 +18 0.118000000000000 0.238000000000000 0 +20 0.212400000000000 0.282000000000000 0 +22 0.310300000000000 0.329000000000000 0 +25 0.461800000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 + +Reynolds Number: 4e4 +BV Dyn. Stall Model - Positive Stall AOA (deg): 3.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -3.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 4.309 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 0.526 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -0.526 +AOA (deg) CL CD Cm25 +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -0.480200000000000 0.405000000000000 0 +-22 -0.334500000000000 0.329000000000000 0 +-20 -0.241400000000000 0.282000000000000 0 +-18 -0.161900000000000 0.238000000000000 0 +-16 -0.0981000000000000 0.196000000000000 0 +-14 -0.0833000000000000 0.158000000000000 0 +-12 -0.166000000000000 0.123000000000000 0 +-10 -0.269100000000000 0.0620000000000000 0 +-9 -0.316200000000000 0.0343000000000000 0 +-8 -0.342000000000000 0.0319000000000000 0 +-7 -0.342700000000000 0.0297000000000000 0 +-6 -0.338200000000000 0.0279000000000000 0 +-5 -0.308600000000000 0.0264000000000000 0 +-4 -0.273000000000000 0.0253000000000000 0 +-3 -0.210300000000000 0.0243000000000000 0 +-2 -0.146500000000000 0.0237000000000000 0 +-1 -0.0752000000000000 0.0233000000000000 0 +0 0 0.0232000000000000 0 +1 0.0752000000000000 0.0233000000000000 0 +2 0.146500000000000 0.0237000000000000 0 +3 0.210300000000000 0.0243000000000000 0 +4 0.273000000000000 0.0253000000000000 0 +5 0.308600000000000 0.0264000000000000 0 +6 0.338200000000000 0.0279000000000000 0 +7 0.342700000000000 0.0297000000000000 0 +8 0.342000000000000 0.0319000000000000 0 +9 0.316200000000000 0.0343000000000000 0 +10 0.269100000000000 0.0620000000000000 0 +12 0.166000000000000 0.123000000000000 0 +14 0.0833000000000000 0.158000000000000 0 +16 0.0981000000000000 0.196000000000000 0 +18 0.161900000000000 0.238000000000000 0 +20 0.241400000000000 0.282000000000000 0 +22 0.334500000000000 0.329000000000000 0 +25 0.480200000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 + +Reynolds Number: 8e4 +BV Dyn. Stall Model - Positive Stall AOA (deg): 4.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -4.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 5.277 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 0.829 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -0.829 +AOA (deg) CL CD Cm25 +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -0.529700000000000 0.405000000000000 0 +-22 -0.409100000000000 0.329000000000000 0 +-20 -0.347500000000000 0.282000000000000 0 +-18 -0.322100000000000 0.238000000000000 0 +-16 -0.349900000000000 0.196000000000000 0 +-14 -0.429600000000000 0.158000000000000 0 +-12 -0.522800000000000 0.123000000000000 0 +-11 -0.556400000000000 0.0700000000000000 0 +-10 -0.578000000000000 0.0297000000000000 0 +-9 -0.587400000000000 0.0273000000000000 0 +-8 -0.575100000000000 0.0252000000000000 0 +-7 -0.544500000000000 0.0233000000000000 0 +-6 -0.495300000000000 0.0217000000000000 0 +-5 -0.432400000000000 0.0204000000000000 0 +-4 -0.356400000000000 0.0194000000000000 0 +-3 -0.273100000000000 0.0186000000000000 0 +-2 -0.183900000000000 0.0181000000000000 0 +-1 -0.0921000000000000 0.0178000000000000 0 +0 0 0.0177000000000000 0 +1 0.0921000000000000 0.0178000000000000 0 +2 0.183900000000000 0.0181000000000000 0 +3 0.273100000000000 0.0186000000000000 0 +4 0.356400000000000 0.0194000000000000 0 +5 0.432400000000000 0.0204000000000000 0 +6 0.495300000000000 0.0217000000000000 0 +7 0.544500000000000 0.0233000000000000 0 +8 0.575100000000000 0.0252000000000000 0 +9 0.587400000000000 0.0273000000000000 0 +10 0.578000000000000 0.0297000000000000 0 +11 0.556400000000000 0.0700000000000000 0 +12 0.522800000000000 0.123000000000000 0 +14 0.429600000000000 0.158000000000000 0 +16 0.349900000000000 0.196000000000000 0 +18 0.322100000000000 0.238000000000000 0 +20 0.347500000000000 0.282000000000000 0 +22 0.409100000000000 0.329000000000000 0 +25 0.529700000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 + +Reynolds Number: 1.6e5 +BV Dyn. Stall Model - Positive Stall AOA (deg): 5.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -5.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 5.371 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.031 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.031 +AOA (deg) CL CD Cm25 +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -0.666400000000000 0.405000000000000 0 +-22 -0.602300000000000 0.329000000000000 0 +-20 -0.592000000000000 0.282000000000000 0 +-18 -0.609800000000000 0.238000000000000 0 +-16 -0.648700000000000 0.196000000000000 0 +-14 -0.699300000000000 0.158000000000000 0 +-13 -0.725500000000000 0.0860000000000000 0 +-12 -0.736300000000000 0.0292000000000000 0 +-11 -0.744300000000000 0.0266000000000000 0 +-10 -0.737400000000000 0.0243000000000000 0 +-9 -0.714800000000000 0.0222000000000000 0 +-8 -0.674500000000000 0.0204000000000000 0 +-7 -0.620900000000000 0.0187000000000000 0 +-6 -0.548600000000000 0.0174000000000000 0 +-5 -0.468700000000000 0.0163000000000000 0 +-4 -0.380000000000000 0.0155000000000000 0 +-3 -0.286100000000000 0.0148000000000000 0 +-2 -0.187900000000000 0.0143000000000000 0 +-1 -0.0842000000000000 0.0140000000000000 0 +0 0 0.0139000000000000 0 +1 0.0842000000000000 0.0140000000000000 0 +2 0.187900000000000 0.0143000000000000 0 +3 0.286100000000000 0.0148000000000000 0 +4 0.380000000000000 0.0155000000000000 0 +5 0.468700000000000 0.0163000000000000 0 +6 0.548600000000000 0.0174000000000000 0 +7 0.620900000000000 0.0187000000000000 0 +8 0.674500000000000 0.0204000000000000 0 +9 0.714800000000000 0.0222000000000000 0 +10 0.737400000000000 0.0243000000000000 0 +11 0.744300000000000 0.0266000000000000 0 +12 0.736300000000000 0.0292000000000000 0 +13 0.725500000000000 0.0860000000000000 0 +14 0.699300000000000 0.158000000000000 0 +16 0.648700000000000 0.196000000000000 0 +18 0.609800000000000 0.238000000000000 0 +20 0.592000000000000 0.282000000000000 0 +22 0.602300000000000 0.329000000000000 0 +25 0.666400000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 + +Reynolds Number: 3.6e5 +BV Dyn. Stall Model - Positive Stall AOA (deg): 5.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -5.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.32 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.32 +AOA (deg) CL CD Cm25 +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -0.886600000000000 0.405000000000000 0 +-22 -0.845300000000000 0.329000000000000 0 +-20 -0.839700000000000 0.282000000000000 0 +-18 -0.848900000000000 0.238000000000000 0 +-16 -0.871700000000000 0.196000000000000 0 +-15 -0.884000000000000 0.104000000000000 0 +-14 -0.893700000000000 0.0286000000000000 0 +-13 -0.897300000000000 0.0260000000000000 0 +-12 -0.893800000000000 0.0237000000000000 0 +-11 -0.877900000000000 0.0215000000000000 0 +-10 -0.850000000000000 0.0195000000000000 0 +-9 -0.802600000000000 0.0178000000000000 0 +-8 -0.743400000000000 0.0163000000000000 0 +-7 -0.672800000000000 0.0149000000000000 0 +-6 -0.589100000000000 0.0138000000000000 0 +-5 -0.499800000000000 0.0129000000000000 0 +-4 -0.404400000000000 0.0122000000000000 0 +-3 -0.302400000000000 0.0117000000000000 0 +-2 -0.220000000000000 0.0113000000000000 0 +-1 -0.110000000000000 0.0111000000000000 0 +0 0 0.0111000000000000 0 +1 0.110000000000000 0.0111000000000000 0 +2 0.220000000000000 0.0113000000000000 0 +3 0.302400000000000 0.0117000000000000 0 +4 0.404400000000000 0.0122000000000000 0 +5 0.499800000000000 0.0129000000000000 0 +6 0.589100000000000 0.0138000000000000 0 +7 0.672800000000000 0.0149000000000000 0 +8 0.743400000000000 0.0163000000000000 0 +9 0.802600000000000 0.0178000000000000 0 +10 0.850000000000000 0.0195000000000000 0 +11 0.877900000000000 0.0215000000000000 0 +12 0.893800000000000 0.0237000000000000 0 +13 0.897300000000000 0.0260000000000000 0 +14 0.893700000000000 0.0286000000000000 0 +15 0.884000000000000 0.104000000000000 0 +16 0.871700000000000 0.196000000000000 0 +18 0.848900000000000 0.238000000000000 0 +20 0.839700000000000 0.282000000000000 0 +22 0.845300000000000 0.329000000000000 0 +25 0.886600000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 + +Reynolds Number: 7e5 +BV Dyn. Stall Model - Positive Stall AOA (deg): 6.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -6.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.54 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.54 +AOA (deg) CL CD Cm25 +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -1.03500000000000 0.405000000000000 0 +-22 -0.994000000000000 0.329000000000000 0 +-20 -0.985800000000000 0.282000000000000 0 +-18 -0.991100000000000 0.238000000000000 0 +-17 -0.997300000000000 0.125000000000000 0 +-16 -1.00560000000000 0.0295000000000000 0 +-15 -1.01060000000000 0.0269000000000000 0 +-14 -1.01220000000000 0.0244000000000000 0 +-13 -1.00200000000000 0.0223000000000000 0 +-12 -0.984300000000000 0.0202000000000000 0 +-11 -0.954300000000000 0.0184000000000000 0 +-10 -0.909100000000000 0.0166000000000000 0 +-9 -0.849800000000000 0.0152000000000000 0 +-8 -0.780200000000000 0.0138000000000000 0 +-7 -0.698800000000000 0.0126000000000000 0 +-6 -0.610000000000000 0.0117000000000000 0 +-5 -0.514600000000000 0.0109000000000000 0 +-4 -0.412800000000000 0.0103000000000000 0 +-3 -0.330000000000000 0.00980000000000000 0 +-2 -0.220000000000000 0.00960000000000000 0 +-1 -0.110000000000000 0.00940000000000000 0 +0 0 0.00940000000000000 0 +1 0.110000000000000 0.00940000000000000 0 +2 0.220000000000000 0.00960000000000000 0 +3 0.330000000000000 0.00980000000000000 0 +4 0.412800000000000 0.0103000000000000 0 +5 0.514600000000000 0.0109000000000000 0 +6 0.610000000000000 0.0117000000000000 0 +7 0.698800000000000 0.0126000000000000 0 +8 0.780200000000000 0.0138000000000000 0 +9 0.849800000000000 0.0152000000000000 0 +10 0.909100000000000 0.0166000000000000 0 +11 0.954300000000000 0.0184000000000000 0 +12 0.984300000000000 0.0202000000000000 0 +13 1.00200000000000 0.0223000000000000 0 +14 1.01220000000000 0.0244000000000000 0 +15 1.01060000000000 0.0269000000000000 0 +16 1.00560000000000 0.0295000000000000 0 +17 0.997300000000000 0.125000000000000 0 +18 0.991100000000000 0.238000000000000 0 +20 0.985800000000000 0.282000000000000 0 +22 0.994000000000000 0.329000000000000 0 +25 1.03500000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 + +Reynolds Number: 1e6 +BV Dyn. Stall Model - Positive Stall AOA (deg): 6.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -6.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.65 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.65 +AOA (deg) CL CD Cm25 +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -1.10180000000000 0.405000000000000 0 +-22 -1.06440000000000 0.329000000000000 0 +-20 -1.05540000000000 0.282000000000000 0 +-18 -1.05880000000000 0.135000000000000 0 +-17 -1.06410000000000 0.0300000000000000 0 +-16 -1.06900000000000 0.0273000000000000 0 +-15 -1.07090000000000 0.0248000000000000 0 +-14 -1.06570000000000 0.0226000000000000 0 +-13 -1.04920000000000 0.0206000000000000 0 +-12 -1.02570000000000 0.0187000000000000 0 +-11 -0.986200000000000 0.0170000000000000 0 +-10 -0.936400000000000 0.0154000000000000 0 +-9 -0.869400000000000 0.0140000000000000 0 +-8 -0.793900000000000 0.0128000000000000 0 +-7 -0.710200000000000 0.0117000000000000 0 +-6 -0.619100000000000 0.0108000000000000 0 +-5 -0.519200000000000 0.0101000000000000 0 +-4 -0.440000000000000 0.00960000000000000 0 +-3 -0.330000000000000 0.00920000000000000 0 +-2 -0.220000000000000 0.00900000000000000 0 +-1 -0.110000000000000 0.00890000000000000 0 +0 0 0.00890000000000000 0 +1 0.110000000000000 0.00890000000000000 0 +2 0.220000000000000 0.00900000000000000 0 +3 0.330000000000000 0.00920000000000000 0 +4 0.440000000000000 0.00960000000000000 0 +5 0.519200000000000 0.0101000000000000 0 +6 0.619100000000000 0.0108000000000000 0 +7 0.710200000000000 0.0117000000000000 0 +8 0.793900000000000 0.0128000000000000 0 +9 0.869400000000000 0.0140000000000000 0 +10 0.936400000000000 0.0154000000000000 0 +11 0.986200000000000 0.0170000000000000 0 +12 1.02570000000000 0.0187000000000000 0 +13 1.04920000000000 0.0206000000000000 0 +14 1.06570000000000 0.0226000000000000 0 +15 1.07090000000000 0.0248000000000000 0 +16 1.06900000000000 0.0273000000000000 0 +17 1.06410000000000 0.0300000000000000 0 +18 1.05880000000000 0.135000000000000 0 +20 1.05540000000000 0.282000000000000 0 +22 1.06440000000000 0.329000000000000 0 +25 1.10180000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 + +Reynolds Number: 2e6 +BV Dyn. Stall Model - Positive Stall AOA (deg): 6.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -6.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.65 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.65 +AOA (deg) CL CD Cm25 +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -1.22300000000000 0.405000000000000 0 +-22 -1.18930000000000 0.329000000000000 0 +-20 -1.18120000000000 0.282000000000000 0 +-19 -1.17970000000000 0.145000000000000 0 +-18 -1.18140000000000 0.0285000000000000 0 +-17 -1.18240000000000 0.0260000000000000 0 +-16 -1.18230000000000 0.0236000000000000 0 +-15 -1.17470000000000 0.0215000000000000 0 +-14 -1.15800000000000 0.0196000000000000 0 +-13 -1.13050000000000 0.0179000000000000 0 +-12 -1.09060000000000 0.0162000000000000 0 +-11 -1.03980000000000 0.0148000000000000 0 +-10 -0.973900000000000 0.0135000000000000 0 +-9 -0.898600000000000 0.0124000000000000 0 +-8 -0.814300000000000 0.0114000000000000 0 +-7 -0.725400000000000 0.0105000000000000 0 +-6 -0.626800000000000 0.00980000000000000 0 +-5 -0.550000000000000 0.00920000000000000 0 +-4 -0.440000000000000 0.00890000000000000 0 +-3 -0.330000000000000 0.00860000000000000 0 +-2 -0.220000000000000 0.00840000000000000 0 +-1 -0.110000000000000 0.00830000000000000 0 +0 0 0.00820000000000000 0 +1 0.110000000000000 0.00830000000000000 0 +2 0.220000000000000 0.00840000000000000 0 +3 0.330000000000000 0.00860000000000000 0 +4 0.440000000000000 0.00890000000000000 0 +5 0.550000000000000 0.00920000000000000 0 +6 0.626800000000000 0.00980000000000000 0 +7 0.725400000000000 0.0105000000000000 0 +8 0.814300000000000 0.0114000000000000 0 +9 0.898600000000000 0.0124000000000000 0 +10 0.973900000000000 0.0135000000000000 0 +11 1.03980000000000 0.0148000000000000 0 +12 1.09060000000000 0.0162000000000000 0 +13 1.13050000000000 0.0179000000000000 0 +14 1.15800000000000 0.0196000000000000 0 +15 1.17470000000000 0.0215000000000000 0 +16 1.18230000000000 0.0236000000000000 0 +17 1.18240000000000 0.0260000000000000 0 +18 1.18140000000000 0.0285000000000000 0 +19 1.17970000000000 0.145000000000000 0 +20 1.18120000000000 0.282000000000000 0 +22 1.18930000000000 0.329000000000000 0 +25 1.22300000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 + +Reynolds Number: 5e6 +BV Dyn. Stall Model - Positive Stall AOA (deg): 6.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -6.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.76 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.76 +AOA (deg) CL CD Cm25 +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -1.34760000000000 0.405000000000000 0 +-22 -1.31300000000000 0.329000000000000 0 +-20 -1.30540000000000 0.0293000000000000 0 +-19 -1.30660000000000 0.0268000000000000 0 +-18 -1.30310000000000 0.0245000000000000 0 +-17 -1.29770000000000 0.0224000000000000 0 +-16 -1.28600000000000 0.0205000000000000 0 +-15 -1.26800000000000 0.0186000000000000 0 +-14 -1.24100000000000 0.0170000000000000 0 +-13 -1.19790000000000 0.0156000000000000 0 +-12 -1.14530000000000 0.0143000000000000 0 +-11 -1.07870000000000 0.0132000000000000 0 +-10 -1.00490000000000 0.0121000000000000 0 +-9 -0.922200000000000 0.0112000000000000 0 +-8 -0.833400000000000 0.0104000000000000 0 +-7 -0.735400000000000 0.00970000000000000 0 +-6 -0.660000000000000 0.00910000000000000 0 +-5 -0.550000000000000 0.00860000000000000 0 +-4 -0.440000000000000 0.00830000000000000 0 +-3 -0.330000000000000 0.00810000000000000 0 +-2 -0.220000000000000 0.00790000000000000 0 +-1 -0.110000000000000 0.00780000000000000 0 +0 0 0.00780000000000000 0 +1 0.110000000000000 0.00780000000000000 0 +2 0.220000000000000 0.00790000000000000 0 +3 0.330000000000000 0.00810000000000000 0 +4 0.440000000000000 0.00830000000000000 0 +5 0.550000000000000 0.00860000000000000 0 +6 0.660000000000000 0.00910000000000000 0 +7 0.735400000000000 0.00970000000000000 0 +8 0.833400000000000 0.0104000000000000 0 +9 0.922200000000000 0.0112000000000000 0 +10 1.00490000000000 0.0121000000000000 0 +11 1.07870000000000 0.0132000000000000 0 +12 1.14530000000000 0.0143000000000000 0 +13 1.19790000000000 0.0156000000000000 0 +14 1.24100000000000 0.0170000000000000 0 +15 1.26800000000000 0.0186000000000000 0 +16 1.28600000000000 0.0205000000000000 0 +17 1.29770000000000 0.0224000000000000 0 +18 1.30310000000000 0.0245000000000000 0 +19 1.30660000000000 0.0268000000000000 0 +20 1.30540000000000 0.0293000000000000 0 +22 1.31300000000000 0.329000000000000 0 +25 1.34760000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 + +Reynolds Number: 8e6 +BV Dyn. Stall Model - Positive Stall AOA (deg): 10.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -10.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.131 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.82 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.82 +AOA (deg) CL CD Cm25 +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-22 -1.45100000000000 0.329000000000000 0 +-20 -1.43500000000000 0.282000000000000 0 +-18 -1.41500000000000 0.135000000000000 0 +-16 -1.37700000000000 0.0199000000000000 0 +-15 -1.34400000000000 0.0184000000000000 0 +-14 -1.30100000000000 0.0170000000000000 0 +-13 -1.24800000000000 0.0157000000000000 0 +-12 -1.18200000000000 0.0145000000000000 0 +-11 -1.10800000000000 0.0134000000000000 0 +-10 -1.02400000000000 0.0124000000000000 0 +-9 -0.935000000000000 0.0115000000000000 0 +-8 -0.841000000000000 0.0107000000000000 0 +-7 -0.744000000000000 0.00990000000000000 0 +-6 -0.639000000000000 0.00930000000000000 0 +-5 -0.533000000000000 0.00880000000000000 0 +-4 -0.426000000000000 0.00840000000000000 0 +-3 -0.320000000000000 0.00800000000000000 0 +-2 -0.213000000000000 0.00780000000000000 0 +-1 -0.107000000000000 0.00770000000000000 0 +0 0 0.00760000000000000 0 +1 0.107000000000000 0.00770000000000000 0 +2 0.213000000000000 0.00780000000000000 0 +3 0.320000000000000 0.00800000000000000 0 +4 0.426000000000000 0.00840000000000000 0 +5 0.533000000000000 0.00880000000000000 0 +6 0.639000000000000 0.00930000000000000 0 +7 0.744000000000000 0.00990000000000000 0 +8 0.841000000000000 0.0107000000000000 0 +9 0.935000000000000 0.0115000000000000 0 +10 1.02400000000000 0.0124000000000000 0 +11 1.10800000000000 0.0134000000000000 0 +12 1.18200000000000 0.0145000000000000 0 +13 1.24800000000000 0.0157000000000000 0 +14 1.30100000000000 0.0170000000000000 0 +15 1.34400000000000 0.0184000000000000 0 +16 1.37700000000000 0.0199000000000000 0 +18 1.41500000000000 0.135000000000000 0 +20 1.43500000000000 0.282000000000000 0 +22 1.45100000000000 0.329000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 diff --git a/examples/literate/A_simplyRunningOWENS.jl b/examples/literate/A_simplyRunningOWENS.jl index c9109195..c1cb5628 100644 --- a/examples/literate/A_simplyRunningOWENS.jl +++ b/examples/literate/A_simplyRunningOWENS.jl @@ -21,7 +21,7 @@ import OWENS runpath = path = "/home/runner/work/OWENS.jl/OWENS.jl/examples/literate" # to run locally, change to splitdir(@__FILE__)[1] -##runpath = path = splitdir(@__FILE__)[1] +# runpath = path = splitdir(@__FILE__)[1] modelopt = OWENS.ModelingOptions("$(path)/OWENS_Opt.yml") designparams = OWENS.Design_Data("$path/WINDIO_example.yaml") diff --git a/examples/literate/E_RM2_Medium.jl b/examples/literate/E_RM2_Medium.jl new file mode 100644 index 00000000..eb3fdcd7 --- /dev/null +++ b/examples/literate/E_RM2_Medium.jl @@ -0,0 +1,389 @@ + +# # [Marine Hydrokinetic RM2](@id RM2) +# +# In this example we use the OWENS scripting method to model the RM2 turbine, +# based on “Experimental Study of a Reference Model Vertical-Axis Cross-Flow Turbine”, 2016, Bachant et al. +# While the windio modeling option based on input yaml files is also included in the OWENS.jl/examples directory, +# The scripting method enable much more flexibility and the ability to add detailed comments on the setup and use. +# Note that the documentation contains an API reference for nearly all of the functions where more details can be found +# also accessed via the julia REPL by loading the module of interest, and: ? ModuleName.functionname() +# +# ![](../assets/RM2_wake.png) +#- +#md # !!! tip +#md # This example is also available as a Jupyter notebook +#- + +# Load in all of the modules that we'll be using, and prettify the plotting options +import OWENS +import OWENSAero +import DelimitedFiles +using Statistics:mean +using Test +import FLOWMath + +## import PyPlot +## PyPlot.pygui(true) +## PyPlot.rc("figure", figsize=(4.5, 3)) +## PyPlot.rc("font", size=10.0) +## PyPlot.rc("lines", linewidth=1.5) +## PyPlot.rc("lines", markersize=3.0) +## PyPlot.rc("legend", frameon=false) +## PyPlot.rc("axes.spines", right=false, top=false) +## PyPlot.rc("figure.subplot", left=.18, bottom=.17, top=0.9, right=.9) +## PyPlot.rc("figure",max_open_warning=500) +## plot_cycle=["#348ABD", "#A60628", "#009E73", "#7A68A6", "#D55E00", "#CC79A7"] + +## path = runpath = splitdir(@__FILE__)[1] +runpath = path = "/home/runner/work/OWENS.jl/OWENS.jl/examples/literate" # to run locally, change to splitdir(@__FILE__)[1] + +nothing + +# Here we set the parametric inputs to the preprocessing and run methods. Defaults are used otherwise +# Note that for the OpenFAST coupling, such as adi_lib, setting these to nothing will force the program +# to use the precompiled binaries that are part of the OWENS installation. +# Again, please refer the to API reference for more detailed options of inputs, but of note is that we are +# running with AeroModel = "AD" which will automatically generate all of the AeroDyn files necessary to run the +# structural definition generated here. Also note that this scripting method relys on the NuMAD formatted CSV files +# for the composite layup that gets run through PreComp.jl to calculate the sectional properties. Finally, this +# has been shortened to enable automated deployment, update as desired. + +turbineType = "H-VAWT" # turbine type, for the automatic meshing +Vinf = 1.2 # inflow velocity +TSRrange = [3.0]#LinRange(1.0,5.0,2) range of tip speed ratios +Nslices = 20 # vertical discretizations if DMS or AC aero model +ntheta = 30 # azimuthal discretizations if DMS or AC aero model +structuralModel = "GX" +ntelem = 100 # tower elements +nbelem = 30 # blade elements +nselem = 10 # strut elements +ifw = false # use inflow wind, if DMS or AC aero model +numTS = 20#321 # number of simulation time steps +delta_t = 0.01 # simulation time step spacing +adi_lib = nothing#"$path/../../../../openfast/build/modules/aerodyn/libaerodyn_inflow_c_binding" +adi_rootname = "$path/RM2" # path and name that all the aerodyn files are saved with +VTKsaveName = "$path/vtk/RM2_medium" # path and name that all OWENS VTK files are saved with +tsave_idx = 1:1:numTS-1 #you don't have to save every timestep in VTK +ifw_libfile = nothing#"$path/../../../openfast/build/modules/inflowwind/libifw_c_binding" +fluid_density = 1000.0 +fluid_dyn_viscosity = 1.792E-3 +AddedMass_Coeff_Ca = 1.0 #For structural side added mass +Aero_Buoyancy_Active = true # For buoyancy forcing, handled by the OWENSAero module +AeroModel = "AD" +verbosity = 1 # verbosity level where higher is more +if AeroModel=="AD" + AD15On = true +else + AD15On = false +end + +eta = 0.5 # blade-strut mount point ratio, fraction from leading edge +number_of_blades = 3 # number of blades +towerHeight = 0.2165 # height of the tower past the blades +Blade_Height = 0.807 # height of the blades +Blade_Radius = 0.5375 # radius of the turbine + +NuMad_geom_xlscsv_file_twr = "$path/data_RM2/TowerGeom.csv" # +NuMad_mat_xlscsv_file_twr = "$path/data_RM2/TowerMaterials.csv" +NuMad_geom_xlscsv_file_bld = "$path/data_RM2/GeomBlades$AeroModel.csv" +NuMad_mat_xlscsv_file_bld = "$path/data_RM2/materials_NuMAD.csv" +NuMad_geom_xlscsv_file_strut = "$path/data_RM2/GeomStruts$AeroModel.csv" +NuMad_mat_xlscsv_file_strut = "$path/data_RM2/materials_NuMAD.csv" + +nothing + +# For this simulation, using aerodyn ("AD"), we will use a turbulent inflow file, indicated as WindType 3 +# We can let the built in OWENS library for turbsim generate the file as so. Modify the inp file to your liking and +# comment out the run command to run your own with more time +WindType = 3 +windINPfilename = "$path/data_RM2/3mx3m1pt2msNTM.bts" +run(`$(OWENS.OWENSOpenFASTWrappers.turbsim()) $(windINPfilename[1:end-3])inp`) + +nothing +# Here we would set up to run multiple different inflow conditions, and we can +# allow the preprocessing to re-run each time since it only takes a few seconds. +# The for loop is commented out to enable this example to be parsed by the literate +# package that auto generates the docs. + +CP = zeros(length(TSRrange)) +mymesh = [] +myel = [] +system = [] +assembly = [] +sections = [] +myjoint = [] +pBC = [] +## for (iTSR,TSR) in enumerate(collect(TSRrange)) +TSR = TSRrange[1] +iTSR = 1 + global Vinf + global mymesh + global myel + global system + global assembly + global sections + global myjoint + global pBC + + omega = Vinf/Blade_Radius*TSR + RPM = omega * 60 / (2*pi) + + println(RPM) + + nothing + + # Here we run the OWENS preprocessing, which creates the beam mesh and joints, calculates the sectional properties + # maps the sectional properties to the elements. It also sets up the aero module being used. + + shapeZ = collect(LinRange(0,Blade_Height,Nslices+1)) + helix_angle = 0.0#-pi/4 + shapeX = cos.(shapeZ/maximum(shapeZ)*helix_angle).*Blade_Radius + shapeY = sin.(shapeZ/maximum(shapeZ)*helix_angle).*Blade_Radius + + mymesh,myel,myort,myjoint,sectionPropsArray,mass_twr, mass_bld, + stiff_twr, stiff_bld,bld_precompinput, + bld_precompoutput,plyprops_bld,numadIn_bld,lam_U_bld,lam_L_bld, + twr_precompinput,twr_precompoutput,plyprops_twr,numadIn_twr,lam_U_twr,lam_L_twr,aeroForces,deformAero, + mass_breakout_blds,mass_breakout_twr,system,assembly,sections,AD15bldNdIdxRng, AD15bldElIdxRng = OWENS.setupOWENS(OWENSAero,path; + rho=fluid_density, + mu=fluid_dyn_viscosity, + Nslices, + ntheta, + RPM, + Vinf, + eta, + B=number_of_blades, + H = Blade_Height, + R = Blade_Radius, + shapeZ, + shapeX, + shapeY, + ifw, + WindType, + delta_t, + numTS, + adi_lib, + adi_rootname, + windINPfilename, + ifw_libfile, + NuMad_geom_xlscsv_file_twr, + NuMad_mat_xlscsv_file_twr, + NuMad_geom_xlscsv_file_bld, + NuMad_mat_xlscsv_file_bld, + NuMad_geom_xlscsv_file_strut, + NuMad_mat_xlscsv_file_strut, + Htwr_base=towerHeight, + Htwr_blds = Blade_Height+towerHeight, + ntelem, + nbelem, + nselem, + joint_type = 0, + strut_twr_mountpoint = [0.5], + strut_bld_mountpoint = [0.5], + AeroModel, #AD, DMS, AC + DynamicStallModel="BV", + Aero_AddedMass_Active = false, + Aero_RotAccel_Active = false, + AddedMass_Coeff_Ca, + Aero_Buoyancy_Active, + verbosity, + meshtype = turbineType) + + nothing + + ## This plots the mesh and node numbering of the resulting mesh and overlays the joint connections + + ## PyPlot.figure() + ## for icon = 1:length(mymesh.conn[:,1]) + ## idx1 = mymesh.conn[icon,1] + ## idx2 = mymesh.conn[icon,2] + ## PyPlot.plot3D([mymesh.x[idx1],mymesh.x[idx2]],[mymesh.y[idx1],mymesh.y[idx2]],[mymesh.z[idx1],mymesh.z[idx2]],"k.-") + ## PyPlot.plot3D([1,1],[1,1],[1,1],"k.-") + ## PyPlot.text3D(mymesh.x[idx1].+rand()/30,mymesh.y[idx1].+rand()/30,mymesh.z[idx1].+rand()/30,"$idx1",ha="center",va="center") + ## end + ## for ijoint = 1:length(myjoint[:,1]) + ## idx2 = Int(myjoint[ijoint,2]) + ## idx1 = Int(myjoint[ijoint,3]) + ## PyPlot.plot3D([mymesh.x[idx1],mymesh.x[idx2]],[mymesh.y[idx1],mymesh.y[idx2]],[mymesh.z[idx1],mymesh.z[idx2]],"r.-") + ## PyPlot.text3D(mymesh.x[idx1].+rand()/30,mymesh.y[idx1].+rand()/30,mymesh.z[idx1].+rand()/30,"$idx1",color="r",ha="center",va="center") + ## PyPlot.text3D(mymesh.x[idx2].+rand()/30,mymesh.y[idx2].+rand()/30,mymesh.z[idx2].+rand()/30,"$idx2",color="r",ha="center",va="center") + ## end + ## PyPlot.xlabel("x") + ## PyPlot.ylabel("y") + ## PyPlot.zlabel("z") + ## PyPlot.axis("equal") + + nothing + + # Here we apply the boundary conditions. For this case, the tower base node which is + # 1 is constrained in all 6 degrees of freedom to have a displacement of 0, and the tower top is also constrained. + # You can change this displacement to allow for things like pretension, and you can apply boundary conditions to any node. + + pBC = [1 1 0 + 1 2 0 + 1 3 0 + 1 4 0 + 1 5 0 + 1 6 0 + AD15bldElIdxRng[1,2]-1 1 0 + AD15bldElIdxRng[1,2]-1 2 0 + AD15bldElIdxRng[1,2]-1 3 0 + AD15bldElIdxRng[1,2]-1 4 0 + AD15bldElIdxRng[1,2]-1 5 0] + + nothing + + # There are inputs for the overall coupled simulation, please see the api reference for specifics on all the options: ? OWENS.Inputs() + + tocp = [0.0;10.0; 1e6] + Omegaocp = [RPM; RPM; RPM]./60 #control inputs + + tocp_Vinf = [0.0;10.0; 1e6] + Vinfocp = [Vinf;Vinf;Vinf] + + inputs = OWENS.Inputs(;verbosity,analysisType = structuralModel, + tocp, + dataOutputFilename = "./InitialDataOutputs_scripting.out", + Omegaocp, + tocp_Vinf, + Vinfocp, + numTS, + delta_t, + AD15On, + aeroLoadsOn = 2, + MAXITER = 20) + + nothing + + # Then there are inputs for the finite element models, also, please see the api reference for specifics on the options + + FEAinputs = OWENS.FEAModel(;analysisType = structuralModel, + dataOutputFilename = "./InitialDataOutputs_scripting.out", + joint = myjoint, + platformTurbineConnectionNodeNumber = 1, + pBC, + nlOn = false, + gravityOn = [0,0,9.81], #positive since the turbine is upside down + numNodes = mymesh.numNodes, + RayleighAlpha = 0.05, + RayleighBeta = 0.05, + AddedMass_Coeff_Ca, + iterationType = "DI") + + nothing + + # Here is where we actually call the unsteady simulation and where owens pulls the aero and structural solutions together + # and propogates things in time. Note that for the sake of quickly deployable docs, a shortened simulation is conducted and the CP will not be correct + + println("Running Unsteady") + t, aziHist,OmegaHist,OmegaDotHist,gbHist,gbDotHist,gbDotDotHist,FReactionHist, + FTwrBsHist,genTorque,genPower,torqueDriveShaft,uHist,uHist_prp,epsilon_x_hist,epsilon_y_hist, + epsilon_z_hist,kappa_x_hist,kappa_y_hist,kappa_z_hist,FPtfmHist,FHydroHist,FMooringHist, + topFexternal_hist,rbDataHist = OWENS.Unsteady_Land(inputs;system,assembly, + topModel=FEAinputs,topMesh=mymesh,topEl=myel,aero=aeroForces,deformAero,turbsimfile = windINPfilename) + + area = Blade_Height*2*Blade_Radius + full_rev_N_timesteps = round(Int,RPM/60/delta_t) + if full_rev_N_timesteps>numTS + idx_start = 1 + else + idx_start = numTS-full_rev_N_timesteps + end + CP[iTSR] = mean(FReactionHist[idx_start:end,6].*OmegaHist[idx_start:end]*2*pi)/(0.5*fluid_density*mean(Vinfocp)^3*area) + TSR = mean(OmegaHist*2*pi*Blade_Radius/mean(Vinfocp)) + ReD = fluid_density*mean(Vinfocp)*Blade_Radius*2/fluid_dyn_viscosity + + nothing + + # We can output vtk files viewable in paraview. Here it is done for each time step and shows the + # deformations. Additionaly, there is a method to input custom values and have them show up on the vtk surface mesh + # for example, strain, or reaction force, etc. This is described in more detail in the api reference for the function + # This helper function looks through all the loads and picks out the worst case safety factor in each of the stacks of composite lamina + # it also calculates analytical simply supported buckling safety factors + + ########################################## + #### Ultimate Failure ##### + ########################################## + + massOwens,stress_U,SF_ult_U,SF_buck_U,stress_L,SF_ult_L,SF_buck_L,stress_TU,SF_ult_TU, + SF_buck_TU,stress_TL,SF_ult_TL,SF_buck_TL,topstrainout_blade_U,topstrainout_blade_L, + topstrainout_tower_U,topstrainout_tower_L,topDamage_blade_U, + topDamage_blade_L,topDamage_tower_U,topDamage_tower_L = OWENS.extractSF(bld_precompinput, + bld_precompoutput,plyprops_bld,numadIn_bld,lam_U_bld,lam_L_bld, + twr_precompinput,twr_precompoutput,plyprops_twr,numadIn_twr,lam_U_twr,lam_L_twr, + mymesh,myel,myort,number_of_blades,epsilon_x_hist,kappa_y_hist,kappa_z_hist,epsilon_z_hist, + kappa_x_hist,epsilon_y_hist;verbosity, #Verbosity 0:no printing, 1: summary, 2: summary and spanwise worst safety factor + Twr_LE_U_idx=1,Twr_LE_L_idx=1, + AD15bldNdIdxRng,AD15bldElIdxRng,strut_precompoutput=nothing) + + OWENS.outputData(;mymesh,inputs,t,aziHist,OmegaHist,OmegaDotHist,gbHist,gbDotHist,gbDotDotHist,FReactionHist,genTorque,genPower,torqueDriveShaft,uHist,uHist_prp,epsilon_x_hist,epsilon_y_hist,epsilon_z_hist,kappa_x_hist,kappa_y_hist,kappa_z_hist,FTwrBsHist,massOwens,stress_U,SF_ult_U,SF_buck_U,stress_L,SF_ult_L,SF_buck_L,stress_TU,SF_ult_TU,SF_buck_TU,stress_TL,SF_ult_TL,SF_buck_TL,topstrainout_blade_U,topstrainout_blade_L,topstrainout_tower_U,topstrainout_tower_L,topDamage_blade_U,topDamage_blade_L,topDamage_tower_U,topDamage_tower_L) + + OWENS.OWENSVTK(VTKsaveName,t,uHist,system,assembly,sections,aziHist,mymesh,myel, + epsilon_x_hist,epsilon_y_hist,epsilon_z_hist,kappa_x_hist,kappa_y_hist,kappa_z_hist, + FReactionHist,topFexternal_hist;tsave_idx) + + +## end + +## PyPlot.figure("CP2") +## PyPlot.plot(TSRrange,CP,".-",color=plot_cycle[2],label="OWENS Aero, 1.3 RE_d (No Added Mass)") #,color=color_cycle[2] +## RM2_0_538D_RE_D_1_3E6 = DelimitedFiles.readdlm("$(path)/data_RM2/RM2_0.538D_RE_D_1.3E6.csv", ',',Float64) +## PyPlot.plot(RM2_0_538D_RE_D_1_3E6[:,1],RM2_0_538D_RE_D_1_3E6[:,2],"k-",label="Exp. 1.3e6 RE_d") +## PyPlot.legend() +## PyPlot.xlabel("TSR") +## PyPlot.ylabel("Cp") + +nothing + +# Here we use the automated campbell diagram function to run the modal analysis of the turbine and save the modeshapes to VTK + +rotSpdArrayRPM = [0.0, 42.64] + +FEAinputs = OWENS.FEAModel(;analysisType = "GX", +dataOutputFilename = "none", +joint = myjoint, +platformTurbineConnectionNodeNumber = 1, +pBC, +nlOn = false, +gravityOn = [0,0,9.81], #positive since the turbine is upside down +numNodes = mymesh.numNodes, +RayleighAlpha = 0.05, +RayleighBeta = 0.05, +AddedMass_Coeff_Ca, +iterationType = "DI") + +freq2 = OWENS.AutoCampbellDiagram(FEAinputs,mymesh,myel,system,assembly,sections; + rotSpdArrayRPM, + VTKsavename=VTKsaveName, + saveModes = [1,3,5], #must be int + saveRPM = [2], #must be int + mode_scaling = 500.0, + ) +freqGX = [freq2[:,i] for i=1:2:FEAinputs.numModes-6-2] + +nothing + +## Now the Campbell diagram can be generated +## NperRevLines = 8 +## PyPlot.figure() +## for i=1:NperRevLines +## linex=[rotSpdArrayRPM[1], rotSpdArrayRPM[end]+5] +## liney=[rotSpdArrayRPM[1], rotSpdArrayRPM[end]+5].*i./60.0 +## PyPlot.plot(linex,liney,"--k",linewidth=0.5) +## PyPlot.annotate("$i P",xy=(0.95*linex[2],liney[2]+.05+(i-1)*.01)) +## end +## PyPlot.grid() +## PyPlot.xlabel("Rotor Speed (RPM)") +## PyPlot.ylabel("Frequency (Hz)") +## PyPlot.plot(0,0,"k-",label="Experimental") +## PyPlot.plot(0,0,color=plot_cycle[1],"-",label="OWENS") +## PyPlot.legend() +# +## for i=1:1:FEAinputs.numModes +## PyPlot.plot(rotSpdArrayRPM,freq2[:,i],color=plot_cycle[2],"-") #plot mode i at various rotor speeds +## end +## PyPlot.plot(0,0,color=plot_cycle[2],"-",label="GXBeam") +## PyPlot.legend(fontsize=8.5,loc = (0.09,0.8),ncol=2,handleheight=1.8, labelspacing=0.03) +## PyPlot.ylim([0,40.0]) + +nothing \ No newline at end of file diff --git a/examples/literate/OWENS_Opt.yml b/examples/literate/OWENS_Opt.yml index ea668078..51501ae3 100644 --- a/examples/literate/OWENS_Opt.yml +++ b/examples/literate/OWENS_Opt.yml @@ -17,8 +17,8 @@ OWENS_Options: Prescribed_Vinf_Vinf_controlpoints: [17.2,17.2] DLC_Options: - DLCs: ["1_1","2_1"] # name of DLC - Vinf_range: [5.0,10.0] # inflow Cutin to cutout and discretization + DLCs: ["1_1"] # name of DLC + Vinf_range: [5.0] # inflow Cutin to cutout and discretization IEC_std: "\"1-ED3\"" # turbsim input file IEC standard WindChar: "\"A\"" # turbsim wind charasteric WindClass: 1 # turbsim wind class @@ -31,7 +31,7 @@ DLC_Options: grid_oversize: 1.1 # amount that the turbsim inflow is oversized compared to the turbine to allow for deflection regenWindFiles: false #, force regeneration of turbsim files even if they already exist delta_t_turbsim: 0.05 # turbsim timestep - simtime_turbsim: 600.0 # turbsim total time, which loops if simtime exceeds turbsim time + simtime_turbsim: 60.0 # turbsim total time, which loops if simtime exceeds turbsim time OWENSAero_Options: Nslices: 20 # number of 3-D slices for the strip method to go from 2D to 3D considering curved deforming blades diff --git a/examples/literate/airfoils/NACA_0021_AD.csv b/examples/literate/airfoils/NACA_0021_AD.csv new file mode 100644 index 00000000..2e840158 --- /dev/null +++ b/examples/literate/airfoils/NACA_0021_AD.csv @@ -0,0 +1,34 @@ +100,0.0 +95,-1.412 +90,-2.534 +80,-4.591 +70,-6.412 +60,-7.986 +50,-9.265 +40,-10.156 +30,-10.504 +25,-10.397 +20,-10.04 +15,-9.354 +10,-8.195 +7.5,-7.35 +5,-6.221 +2.5,-4.576 +1.25,-3.315 +0,0 +1.25,3.315 +2.5,4.576 +5,6.221 +7.5,7.35 +10,8.195 +15,9.354 +20,10.04 +25,10.397 +30,10.504 +40,10.156 +50,9.265 +60,7.986 +70,6.412 +80,4.591 +90,2.534 +95,1.412 \ No newline at end of file diff --git a/examples/literate/airfoils/NACA_0021_AD.dat b/examples/literate/airfoils/NACA_0021_AD.dat new file mode 100644 index 00000000..3b9e99ec --- /dev/null +++ b/examples/literate/airfoils/NACA_0021_AD.dat @@ -0,0 +1,1551 @@ +! ------------ AirfoilInfo v1.01.x Input File ---------------------------------- +! NACA 0018 at Re = 0.01,0.02,0.04,0.08,0.16,0.36,0.70,1,2,5 million +! line +! line +! ------------------------------------------------------------------------------ +DEFAULT InterpOrd - ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] +0.18 RelThickness - ! The non-dimensional thickness of the airfoil (thickness/chord) [only used if UAMod=7] [default=0.2] (-) +1 NonDimArea - ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) +@"NACA_0021_AD.txt" NumCoords - ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +"NA" BL_file - ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. +7 NumTabs - ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. +! ------------------------------------------------------------------------------ +! data for table +! ------------------------------------------------------------------------------ +0.05 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +3.0 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-3.0 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.4757 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-0.4757 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0214 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +160 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -0.480200000000000 0.405000000000000 0 +-22 -0.334500000000000 0.329000000000000 0 +-20 -0.241400000000000 0.282000000000000 0 +-18 -0.161900000000000 0.238000000000000 0 +-16 -0.0981000000000000 0.196000000000000 0 +-14 -0.0833000000000000 0.158000000000000 0 +-12 -0.166000000000000 0.123000000000000 0 +-10.500 -0.3112 0.12560 0.11631 +-10.250 -0.2843 0.12215 0.11285 +-10.000 -0.3247 0.12282 0.11357 +-9.750 -0.2690 0.11676 0.10748 +-9.500 -0.2967 0.11674 0.10749 +-9.250 -0.2590 0.11173 0.10247 +-9.000 -0.2672 0.11069 0.10145 +-8.750 -0.3659 0.09402 0.08467 +-8.500 -0.3767 0.09022 0.08089 +-8.250 -0.4033 0.08534 0.07605 +-8.000 -0.4715 0.07745 0.06824 +-7.750 -0.4041 0.08041 0.07119 +-7.500 -0.4468 0.07517 0.06603 +-7.250 -0.6906 0.05799 0.04907 +-7.000 -0.8363 0.04920 0.04010 +-6.750 -0.7209 0.05447 0.04562 +-6.500 -0.8240 0.04776 0.03872 +-6.250 -0.7822 0.04914 0.04024 +-6.000 -0.8189 0.04596 0.03692 +-5.750 -0.7958 0.04632 0.03739 +-5.500 -0.8154 0.04402 0.03493 +-5.250 -0.7909 0.04456 0.03561 +-5.000 -0.8085 0.04222 0.03308 +-4.750 -0.7788 0.04326 0.03431 +-4.500 -0.7837 0.04171 0.03266 +-4.250 -0.7645 0.04213 0.03318 +-4.000 -0.7592 0.04136 0.03238 +-3.750 -0.7521 0.04079 0.03179 +-3.500 -0.7355 0.04107 0.03215 +-3.250 -0.7304 0.04029 0.03132 +-3.000 -0.6987 0.04088 0.03197 +-2.750 -0.6416 0.04215 0.03328 +-2.500 -0.5915 0.04298 0.03411 +-2.250 -0.5503 0.04341 0.03453 +-2.000 -0.5136 0.04365 0.03474 +-1.750 -0.4532 0.04526 0.03640 +-1.500 -0.3880 0.04646 0.03760 +-1.250 -0.3540 0.04667 0.03780 +-1.000 -0.3318 0.04665 0.03775 +-0.750 -0.2325 0.04876 0.03989 +-0.500 -0.1461 0.04940 0.04050 +-0.250 -0.1393 0.04928 0.04038 +0.000 0.0000 0.05040 0.04152 +0.250 0.1392 0.04928 0.04038 +0.500 0.1463 0.04939 0.04050 +0.750 0.2325 0.04876 0.03988 +1.000 0.3317 0.04665 0.03775 +1.250 0.3539 0.04667 0.03779 +1.500 0.3878 0.04646 0.03760 +1.750 0.4531 0.04526 0.03639 +2.000 0.5135 0.04365 0.03474 +2.250 0.5504 0.04340 0.03452 +2.500 0.5915 0.04297 0.03410 +2.750 0.6416 0.04214 0.03327 +3.000 0.6987 0.04087 0.03195 +3.250 0.7301 0.04029 0.03132 +3.500 0.7353 0.04106 0.03215 +3.750 0.7520 0.04077 0.03176 +4.000 0.7589 0.04135 0.03237 +4.250 0.7643 0.04211 0.03316 +4.500 0.7834 0.04171 0.03265 +4.750 0.7786 0.04325 0.03430 +5.000 0.8081 0.04222 0.03308 +5.250 0.7906 0.04455 0.03560 +5.500 0.8155 0.04398 0.03490 +5.750 0.7955 0.04631 0.03737 +6.000 0.8190 0.04593 0.03689 +6.250 0.7819 0.04913 0.04023 +6.500 0.8243 0.04773 0.03868 +6.750 0.7216 0.05441 0.04555 +7.000 0.6677 0.05811 0.04924 +7.250 0.6916 0.05791 0.04899 +7.500 0.4474 0.07510 0.06595 +7.750 0.4049 0.08033 0.07110 +8.000 0.4721 0.07739 0.06817 +8.250 0.4039 0.08528 0.07599 +8.500 0.3775 0.09015 0.08082 +8.750 0.3673 0.09391 0.08456 +9.000 0.3997 0.09451 0.08514 +9.250 0.3819 0.09944 0.09006 +9.500 0.3752 0.10386 0.09448 +9.750 0.3820 0.10800 0.09863 +10.250 0.2855 0.12214 0.11284 +10.500 0.3127 0.12563 0.11634 +12 0.166000000000000 0.123000000000000 0 +14 0.0833000000000000 0.158000000000000 0 +16 0.0981000000000000 0.196000000000000 0 +18 0.161900000000000 0.238000000000000 0 +20 0.241400000000000 0.282000000000000 0 +22 0.334500000000000 0.329000000000000 0 +25 0.480200000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 +! ------------------------------------------------------------------------------ +! data for table +! ------------------------------------------------------------------------------ +0.1 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +5.0 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-5.0 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.6566 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-0.6566 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0162 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +194 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -0.666400000000000 0.405000000000000 0 +-22 -0.602300000000000 0.329000000000000 0 +-20 -0.592000000000000 0.282000000000000 0 +-18 -0.609800000000000 0.238000000000000 0 +-16.250 -0.5418 0.17959 0.17300 +-16.000 -0.5218 0.17458 0.16798 +-15.750 -1.0757 0.06945 0.06174 +-15.000 -1.0716 0.06221 0.05443 +-14.750 -1.1181 0.05655 0.04843 +-14.500 -1.1584 0.05230 0.04383 +-14.250 -1.1225 0.05198 0.04374 +-14.000 -1.1217 0.05028 0.04198 +-13.750 -1.1410 0.04769 0.03917 +-13.500 -1.1689 0.04524 0.03640 +-13.250 -1.1295 0.04478 0.03622 +-13.000 -1.1311 0.04343 0.03479 +-12.750 -1.1495 0.04176 0.03290 +-12.500 -1.1393 0.04058 0.03175 +-12.250 -1.1243 0.03993 0.03119 +-12.000 -1.1374 0.03889 0.03002 +-11.750 -1.1599 0.03782 0.02870 +-11.500 -1.1248 0.03722 0.02841 +-11.250 -1.1280 0.03641 0.02754 +-11.000 -1.1446 0.03548 0.02634 +-10.750 -1.1160 0.03489 0.02605 +-10.500 -1.1166 0.03422 0.02531 +-10.250 -1.1202 0.03336 0.02431 +-10.000 -1.1022 0.03292 0.02408 +-9.750 -1.1033 0.03226 0.02330 +-9.500 -1.0943 0.03159 0.02268 +-9.250 -1.0843 0.03117 0.02232 +-9.000 -1.0869 0.03049 0.02143 +-8.750 -1.0682 0.03009 0.02126 +-8.500 -1.0638 0.02958 0.02066 +-8.250 -1.0510 0.02910 0.02027 +-8.000 -1.0410 0.02874 0.01992 +-7.750 -1.0310 0.02826 0.01942 +-7.500 -1.0177 0.02799 0.01923 +-7.250 -1.0080 0.02755 0.01873 +-7.000 -0.9930 0.02735 0.01865 +-6.750 -0.9825 0.02698 0.01820 +-6.500 -0.9668 0.02682 0.01818 +-6.250 -0.9284 0.02666 0.01804 +-6.000 -0.8880 0.02654 0.01784 +-5.750 -0.8396 0.02658 0.01805 +-5.500 -0.8021 0.02640 0.01794 +-5.250 -0.7628 0.02623 0.01776 +-5.000 -0.7209 0.02613 0.01771 +-4.750 -0.6844 0.02600 0.01771 +-4.500 -0.6395 0.02580 0.01754 +-4.250 -0.6102 0.02564 0.01736 +-4.000 -0.5600 0.02548 0.01736 +-3.750 -0.5318 0.02530 0.01722 +-3.500 -0.4845 0.02500 0.01692 +-3.250 -0.4524 0.02493 0.01698 +-3.000 -0.4038 0.02461 0.01674 +-2.750 -0.3715 0.02434 0.01647 +-2.500 -0.3309 0.02410 0.01632 +-2.250 -0.2802 0.02367 0.01597 +-2.000 -0.2618 0.02352 0.01582 +-1.750 -0.2139 0.02312 0.01549 +-1.500 -0.1906 0.02308 0.01553 +-1.250 -0.1507 0.02259 0.01501 +-0.750 -0.0906 0.02245 0.01497 +-0.500 -0.0653 0.02229 0.01480 +-0.250 -0.0304 0.02238 0.01495 +0.000 0.0000 0.02216 0.01468 +0.250 0.0304 0.02238 0.01495 +0.500 0.0653 0.02229 0.01480 +0.750 0.0906 0.02245 0.01496 +1.250 0.1507 0.02260 0.01501 +1.500 0.1906 0.02308 0.01553 +1.750 0.2139 0.02312 0.01549 +2.000 0.2618 0.02352 0.01582 +2.250 0.2802 0.02366 0.01597 +2.500 0.3309 0.02410 0.01632 +2.750 0.3713 0.02434 0.01646 +3.000 0.4037 0.02461 0.01674 +3.250 0.4523 0.02492 0.01698 +3.500 0.4844 0.02500 0.01692 +3.750 0.5316 0.02530 0.01722 +4.000 0.5600 0.02548 0.01735 +4.250 0.6101 0.02563 0.01735 +4.500 0.6395 0.02580 0.01754 +4.750 0.6843 0.02599 0.01771 +5.000 0.7209 0.02612 0.01770 +5.250 0.7627 0.02622 0.01775 +5.500 0.8021 0.02639 0.01793 +5.750 0.8394 0.02657 0.01804 +6.000 0.8879 0.02653 0.01783 +6.250 0.9285 0.02665 0.01803 +6.500 0.9665 0.02681 0.01817 +6.750 0.9822 0.02697 0.01819 +7.000 0.9927 0.02734 0.01864 +7.250 1.0077 0.02754 0.01872 +7.500 1.0174 0.02798 0.01922 +7.750 1.0308 0.02825 0.01941 +8.000 1.0408 0.02873 0.01991 +8.250 1.0508 0.02909 0.02026 +8.500 1.0636 0.02957 0.02064 +8.750 1.0680 0.03008 0.02125 +9.000 1.0866 0.03048 0.02142 +9.250 1.0841 0.03116 0.02231 +9.500 1.0941 0.03159 0.02267 +9.750 1.1032 0.03225 0.02329 +10.000 1.1020 0.03291 0.02406 +10.250 1.1200 0.03335 0.02430 +10.500 1.1165 0.03421 0.02530 +10.750 1.1160 0.03488 0.02604 +11.000 1.1445 0.03547 0.02633 +11.250 1.1281 0.03640 0.02753 +11.500 1.1251 0.03721 0.02840 +11.750 1.1600 0.03781 0.02869 +12.000 1.1377 0.03888 0.03001 +12.250 1.1248 0.03992 0.03118 +12.500 1.1405 0.04056 0.03173 +12.750 1.1499 0.04176 0.03290 +13.000 1.1318 0.04342 0.03479 +13.250 1.1308 0.04476 0.03620 +13.500 1.1694 0.04524 0.03641 +13.750 1.1418 0.04770 0.03918 +14.000 1.1230 0.05026 0.04196 +14.250 1.1250 0.05190 0.04364 +14.500 1.1589 0.05233 0.04386 +14.750 1.1189 0.05658 0.04847 +15.000 1.0729 0.06222 0.05445 +15.250 0.5376 0.16648 0.15990 +16 0.648700000000000 0.196000000000000 0 +18 0.609800000000000 0.238000000000000 0 +20 0.592000000000000 0.282000000000000 0 +22 0.602300000000000 0.329000000000000 0 +25 0.666400000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 +! ------------------------------------------------------------------------------ +! data for table +! ------------------------------------------------------------------------------ +0.2 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +5.0 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-5.0 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.787 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-0.787 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0128 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +221 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -0.886600000000000 0.405000000000000 0 +-22 -0.845300000000000 0.329000000000000 0 +-19.500 -1.1826 0.09047 0.08413 -0.0463 +-19.250 -1.2047 0.08434 0.07776 -0.0489 +-19.000 -1.2278 0.07832 0.07145 -0.0514 +-18.750 -1.2032 0.07853 0.07184 -0.0504 +-18.500 -1.1961 0.07650 0.06982 -0.0509 +-18.250 -1.1992 0.07318 0.06640 -0.0518 +-18.000 -1.2090 0.06910 0.06214 -0.0531 +-17.750 -1.2212 0.06488 0.05769 -0.0542 +-17.500 -1.2022 0.06431 0.05727 -0.0537 +-17.250 -1.1971 0.06218 0.05513 -0.0539 +-17.000 -1.1989 0.05930 0.05214 -0.0544 +-16.750 -1.2067 0.05590 0.04852 -0.0549 +-16.500 -1.1937 0.05462 0.04733 -0.0545 +-16.250 -1.1864 0.05287 0.04559 -0.0544 +-16.000 -1.1842 0.05064 0.04328 -0.0543 +-15.750 -1.1871 0.04802 0.04047 -0.0542 +-15.500 -1.1747 0.04673 0.03926 -0.0537 +-15.250 -1.1677 0.04512 0.03766 -0.0533 +-15.000 -1.1645 0.04322 0.03567 -0.0528 +-14.750 -1.1623 0.04128 0.03358 -0.0521 +-14.500 -1.1497 0.04012 0.03253 -0.0515 +-14.250 -1.1433 0.03864 0.03102 -0.0507 +-14.000 -1.1397 0.03701 0.02926 -0.0497 +-13.750 -1.1282 0.03582 0.02813 -0.0488 +-13.500 -1.1203 0.03459 0.02690 -0.0477 +-13.250 -1.1145 0.03330 0.02552 -0.0464 +-13.000 -1.1045 0.03217 0.02440 -0.0451 +-12.750 -1.0959 0.03114 0.02341 -0.0436 +-12.500 -1.0895 0.03011 0.02230 -0.0418 +-12.250 -1.0801 0.02915 0.02135 -0.0401 +-12.000 -1.0725 0.02831 0.02055 -0.0380 +-11.750 -1.0675 0.02752 0.01969 -0.0354 +-11.500 -1.0603 0.02674 0.01895 -0.0329 +-11.250 -1.0561 0.02610 0.01835 -0.0298 +-11.000 -1.0548 0.02555 0.01774 -0.0261 +-10.750 -1.0521 0.02497 0.01719 -0.0224 +-10.500 -1.0534 0.02452 0.01680 -0.0179 +-10.250 -1.0585 0.02419 0.01642 -0.0126 +-10.000 -1.0652 0.02387 0.01607 -0.0069 +-9.750 -1.0728 0.02355 0.01583 -0.0011 +-9.500 -1.0784 0.02330 0.01558 0.0045 +-9.250 -1.0798 0.02308 0.01526 0.0093 +-9.000 -1.0772 0.02265 0.01495 0.0132 +-8.750 -1.0743 0.02239 0.01469 0.0172 +-8.500 -1.0406 0.02193 0.01426 0.0153 +-8.250 -1.0014 0.02161 0.01391 0.0124 +-8.000 -0.9676 0.02111 0.01352 0.0106 +-7.750 -0.9285 0.02075 0.01314 0.0078 +-7.500 -0.8926 0.02036 0.01282 0.0057 +-7.250 -0.8568 0.01993 0.01244 0.0037 +-7.000 -0.8148 0.01961 0.01207 0.0006 +-6.750 -0.7844 0.01919 0.01179 -0.0002 +-6.500 -0.7448 0.01880 0.01142 -0.0027 +-6.250 -0.7005 0.01845 0.01107 -0.0062 +-6.000 -0.6726 0.01808 0.01081 -0.0063 +-5.750 -0.6312 0.01769 0.01043 -0.0090 +-5.500 -0.5890 0.01729 0.01007 -0.0118 +-5.250 -0.5649 0.01698 0.00984 -0.0110 +-5.000 -0.5284 0.01663 0.00944 -0.0125 +-4.750 -0.5013 0.01630 0.00924 -0.0121 +-4.500 -0.4704 0.01596 0.00889 -0.0124 +-4.250 -0.4429 0.01569 0.00867 -0.0120 +-4.000 -0.4151 0.01537 0.00839 -0.0117 +-3.750 -0.3892 0.01516 0.00815 -0.0109 +-3.500 -0.3617 0.01487 0.00794 -0.0104 +-3.250 -0.3370 0.01470 0.00772 -0.0095 +-3.000 -0.3091 0.01445 0.00752 -0.0090 +-2.750 -0.2848 0.01429 0.00737 -0.0080 +-2.500 -0.2571 0.01412 0.00718 -0.0075 +-2.250 -0.2326 0.01398 0.00709 -0.0066 +-2.000 -0.2073 0.01389 0.00694 -0.0057 +-1.750 -0.1801 0.01375 0.00684 -0.0052 +-1.500 -0.1557 0.01368 0.00675 -0.0043 +-1.250 -0.1288 0.01360 0.00668 -0.0037 +-1.000 -0.1032 0.01353 0.00661 -0.0029 +-0.750 -0.0783 0.01351 0.00657 -0.0020 +-0.250 -0.0264 0.01344 0.00651 -0.0006 +0.000 0.0000 0.01344 0.00652 0.0000 +0.250 0.0264 0.01344 0.00651 0.0006 +0.750 0.0783 0.01351 0.00657 0.0020 +1.000 0.1032 0.01353 0.00661 0.0029 +1.250 0.1288 0.01360 0.00668 0.0037 +1.500 0.1557 0.01368 0.00675 0.0043 +1.750 0.1801 0.01375 0.00684 0.0052 +2.000 0.2073 0.01389 0.00694 0.0057 +2.250 0.2326 0.01398 0.00709 0.0066 +2.500 0.2571 0.01412 0.00718 0.0075 +2.750 0.2848 0.01429 0.00737 0.0080 +3.000 0.3091 0.01444 0.00752 0.0090 +3.250 0.3371 0.01470 0.00772 0.0095 +3.500 0.3617 0.01486 0.00793 0.0104 +3.750 0.3893 0.01516 0.00815 0.0109 +4.000 0.4151 0.01537 0.00839 0.0116 +4.250 0.4429 0.01568 0.00866 0.0120 +4.500 0.4704 0.01595 0.00889 0.0124 +4.750 0.5013 0.01630 0.00924 0.0121 +5.000 0.5284 0.01663 0.00944 0.0125 +5.250 0.5649 0.01697 0.00983 0.0110 +5.500 0.5891 0.01728 0.01007 0.0118 +5.750 0.6313 0.01769 0.01042 0.0090 +6.000 0.6726 0.01808 0.01081 0.0063 +6.250 0.7006 0.01845 0.01106 0.0062 +6.500 0.7449 0.01880 0.01142 0.0027 +6.750 0.7845 0.01919 0.01178 0.0002 +7.000 0.8149 0.01961 0.01207 -0.0006 +7.250 0.8569 0.01992 0.01244 -0.0038 +7.500 0.8926 0.02035 0.01281 -0.0057 +7.750 0.9287 0.02074 0.01313 -0.0079 +8.000 0.9678 0.02110 0.01351 -0.0106 +8.250 1.0017 0.02160 0.01390 -0.0124 +8.500 1.0409 0.02192 0.01425 -0.0153 +8.750 1.0741 0.02238 0.01468 -0.0171 +9.000 1.0770 0.02264 0.01494 -0.0132 +9.250 1.0797 0.02306 0.01524 -0.0093 +9.500 1.0783 0.02329 0.01557 -0.0045 +9.750 1.0729 0.02354 0.01582 0.0010 +10.000 1.0653 0.02386 0.01606 0.0069 +10.250 1.0586 0.02418 0.01641 0.0126 +10.500 1.0536 0.02451 0.01678 0.0179 +10.750 1.0524 0.02495 0.01718 0.0223 +11.000 1.0551 0.02554 0.01772 0.0260 +11.250 1.0565 0.02609 0.01833 0.0297 +11.500 1.0607 0.02673 0.01893 0.0328 +11.750 1.0680 0.02750 0.01967 0.0354 +12.000 1.0731 0.02829 0.02053 0.0379 +12.250 1.0810 0.02913 0.02133 0.0400 +12.500 1.0904 0.03010 0.02228 0.0417 +12.750 1.0969 0.03112 0.02339 0.0435 +13.000 1.1057 0.03215 0.02438 0.0449 +13.250 1.1157 0.03329 0.02550 0.0462 +13.500 1.1216 0.03457 0.02688 0.0475 +13.750 1.1297 0.03580 0.02810 0.0486 +14.000 1.1411 0.03700 0.02924 0.0495 +14.250 1.1448 0.03862 0.03100 0.0505 +14.500 1.1515 0.04009 0.03250 0.0512 +14.750 1.1647 0.04122 0.03351 0.0519 +15.000 1.1663 0.04320 0.03565 0.0525 +15.250 1.1697 0.04508 0.03762 0.0530 +15.500 1.1770 0.04669 0.03921 0.0534 +15.750 1.1888 0.04802 0.04047 0.0539 +16.000 1.1862 0.05062 0.04326 0.0540 +16.250 1.1888 0.05282 0.04554 0.0541 +16.500 1.1965 0.05454 0.04724 0.0542 +16.750 1.2085 0.05592 0.04855 0.0545 +17.000 1.2012 0.05929 0.05213 0.0540 +17.250 1.1998 0.06212 0.05507 0.0536 +17.500 1.2054 0.06420 0.05716 0.0533 +17.750 1.2264 0.06458 0.05736 0.0540 +18.000 1.2113 0.06911 0.06215 0.0527 +18.250 1.2021 0.07314 0.06636 0.0514 +18.500 1.1994 0.07641 0.06972 0.0505 +18.750 1.2073 0.07835 0.07164 0.0501 +19.000 1.2296 0.07842 0.07155 0.0509 +19.250 1.2067 0.08443 0.07786 0.0485 +20 0.839700000000000 0.282000000000000 0 +22 0.845300000000000 0.329000000000000 0 +25 0.886600000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 +! ------------------------------------------------------------------------------ +! data for table +! ------------------------------------------------------------------------------ +0.5 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +6.0 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-6.0 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.9125 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-0.9125 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0101 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +223 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -1.03500000000000 0.405000000000000 0 +-22 -0.994000000000000 0.329000000000000 0 +-20 -0.985800000000000 0.282000000000000 0 +-19.750 -1.2237 0.09201 0.08687 -0.0351 +-19.500 -1.2258 0.08851 0.08331 -0.0364 +-19.250 -1.2282 0.08499 0.07969 -0.0376 +-19.000 -1.2301 0.08156 0.07618 -0.0387 +-18.750 -1.2347 0.07798 0.07260 -0.0397 +-18.500 -1.2386 0.07438 0.06896 -0.0407 +-18.250 -1.2399 0.07113 0.06565 -0.0416 +-18.000 -1.2400 0.06805 0.06249 -0.0425 +-17.750 -1.2408 0.06492 0.05928 -0.0432 +-17.500 -1.2455 0.06147 0.05582 -0.0439 +-17.250 -1.2466 0.05841 0.05273 -0.0445 +-17.000 -1.2451 0.05568 0.04992 -0.0450 +-16.750 -1.2412 0.05321 0.04736 -0.0454 +-16.500 -1.2432 0.05024 0.04437 -0.0457 +-16.250 -1.2435 0.04749 0.04159 -0.0459 +-16.000 -1.2401 0.04515 0.03921 -0.0461 +-15.750 -1.2336 0.04313 0.03711 -0.0461 +-15.500 -1.2310 0.04083 0.03476 -0.0460 +-15.250 -1.2290 0.03853 0.03245 -0.0458 +-15.000 -1.2228 0.03667 0.03056 -0.0455 +-14.750 -1.2129 0.03516 0.02898 -0.0452 +-14.500 -1.2091 0.03322 0.02702 -0.0446 +-14.250 -1.2032 0.03152 0.02530 -0.0439 +-14.000 -1.1933 0.03017 0.02392 -0.0433 +-13.750 -1.1831 0.02890 0.02260 -0.0425 +-13.500 -1.1771 0.02739 0.02110 -0.0414 +-13.250 -1.1671 0.02624 0.01993 -0.0404 +-13.000 -1.1535 0.02537 0.01900 -0.0394 +-12.750 -1.1475 0.02410 0.01775 -0.0378 +-12.500 -1.1375 0.02317 0.01682 -0.0363 +-12.250 -1.1246 0.02250 0.01610 -0.0348 +-12.000 -1.1200 0.02154 0.01518 -0.0323 +-11.750 -1.1136 0.02086 0.01450 -0.0296 +-11.500 -1.1058 0.02039 0.01399 -0.0268 +-11.250 -1.1078 0.01975 0.01338 -0.0225 +-11.000 -1.1107 0.01929 0.01293 -0.0177 +-10.750 -1.1141 0.01898 0.01260 -0.0127 +-10.500 -1.1224 0.01870 0.01229 -0.0067 +-10.250 -1.0934 0.01806 0.01171 -0.0080 +-10.000 -1.0611 0.01758 0.01122 -0.0096 +-9.750 -1.0285 0.01705 0.01074 -0.0113 +-9.500 -0.9983 0.01656 0.01028 -0.0124 +-9.250 -0.9668 0.01609 0.00984 -0.0138 +-9.000 -0.9330 0.01561 0.00939 -0.0155 +-8.750 -0.8959 0.01519 0.00899 -0.0178 +-8.500 -0.8643 0.01471 0.00856 -0.0190 +-8.250 -0.8319 0.01436 0.00821 -0.0202 +-8.000 -0.8001 0.01385 0.00778 -0.0214 +-7.750 -0.7692 0.01351 0.00745 -0.0222 +-7.500 -0.7466 0.01314 0.00713 -0.0212 +-7.250 -0.7182 0.01282 0.00681 -0.0214 +-7.000 -0.6987 0.01251 0.00655 -0.0197 +-6.750 -0.6738 0.01225 0.00627 -0.0190 +-6.500 -0.6532 0.01198 0.00604 -0.0175 +-6.250 -0.6292 0.01176 0.00580 -0.0166 +-6.000 -0.6071 0.01151 0.00558 -0.0154 +-5.750 -0.5831 0.01132 0.00538 -0.0145 +-5.500 -0.5596 0.01110 0.00517 -0.0135 +-5.250 -0.5355 0.01093 0.00500 -0.0127 +-5.000 -0.5109 0.01076 0.00481 -0.0119 +-4.750 -0.4866 0.01060 0.00467 -0.0111 +-4.500 -0.4615 0.01047 0.00452 -0.0104 +-4.250 -0.4368 0.01033 0.00437 -0.0096 +-4.000 -0.4113 0.01023 0.00425 -0.0090 +-3.750 -0.3865 0.01010 0.00411 -0.0083 +-3.500 -0.3605 0.01003 0.00401 -0.0078 +-3.250 -0.3357 0.00991 0.00391 -0.0071 +-2.750 -0.2845 0.00976 0.00373 -0.0059 +-2.500 -0.2583 0.00972 0.00365 -0.0054 +-2.250 -0.2331 0.00965 0.00358 -0.0048 +-2.000 -0.2069 0.00960 0.00352 -0.0043 +-1.750 -0.1814 0.00956 0.00346 -0.0037 +-1.500 -0.1554 0.00952 0.00342 -0.0032 +-1.250 -0.1295 0.00949 0.00338 -0.0027 +-1.000 -0.1040 0.00947 0.00334 -0.0020 +-0.750 -0.0774 0.00946 0.00332 -0.0016 +-0.500 -0.0521 0.00943 0.00331 -0.0010 +-0.250 -0.0258 0.00944 0.00329 -0.0006 +0.000 0.0000 0.00942 0.00329 0.0000 +0.250 0.0258 0.00944 0.00329 0.0006 +0.500 0.0521 0.00943 0.00331 0.0010 +0.750 0.0774 0.00946 0.00332 0.0016 +1.000 0.1040 0.00947 0.00334 0.0020 +1.250 0.1295 0.00949 0.00338 0.0027 +1.500 0.1555 0.00952 0.00341 0.0032 +1.750 0.1815 0.00956 0.00346 0.0037 +2.000 0.2069 0.00960 0.00352 0.0043 +2.250 0.2331 0.00965 0.00358 0.0048 +2.500 0.2583 0.00972 0.00365 0.0054 +2.750 0.2845 0.00976 0.00373 0.0059 +3.250 0.3357 0.00991 0.00391 0.0071 +3.500 0.3606 0.01003 0.00401 0.0078 +3.750 0.3866 0.01010 0.00411 0.0083 +4.000 0.4114 0.01023 0.00425 0.0090 +4.250 0.4369 0.01033 0.00437 0.0096 +4.500 0.4616 0.01047 0.00452 0.0104 +4.750 0.4867 0.01060 0.00467 0.0111 +5.000 0.5110 0.01076 0.00481 0.0119 +5.250 0.5356 0.01093 0.00500 0.0127 +5.500 0.5598 0.01110 0.00517 0.0135 +5.750 0.5833 0.01132 0.00538 0.0145 +6.000 0.6073 0.01151 0.00558 0.0153 +6.250 0.6294 0.01176 0.00580 0.0166 +6.500 0.6535 0.01198 0.00604 0.0174 +6.750 0.6741 0.01225 0.00627 0.0189 +7.000 0.6990 0.01251 0.00655 0.0196 +7.250 0.7185 0.01282 0.00681 0.0213 +7.500 0.7469 0.01314 0.00712 0.0212 +7.750 0.7695 0.01351 0.00744 0.0221 +8.000 0.8005 0.01385 0.00778 0.0213 +8.250 0.8323 0.01435 0.00821 0.0201 +8.500 0.8646 0.01470 0.00856 0.0190 +8.750 0.8964 0.01519 0.00899 0.0177 +9.000 0.9335 0.01561 0.00939 0.0154 +9.250 0.9673 0.01609 0.00983 0.0136 +9.500 0.9988 0.01656 0.01027 0.0123 +9.750 1.0292 0.01704 0.01073 0.0112 +10.000 1.0618 0.01757 0.01121 0.0095 +10.250 1.0941 0.01805 0.01169 0.0078 +10.500 1.1224 0.01868 0.01227 0.0067 +10.750 1.1141 0.01897 0.01258 0.0127 +11.000 1.1108 0.01927 0.01291 0.0177 +11.250 1.1079 0.01973 0.01335 0.0225 +11.500 1.1062 0.02037 0.01396 0.0267 +11.750 1.1141 0.02084 0.01448 0.0295 +12.000 1.1207 0.02152 0.01515 0.0322 +12.250 1.1256 0.02247 0.01607 0.0346 +12.500 1.1386 0.02315 0.01680 0.0361 +12.750 1.1487 0.02408 0.01773 0.0376 +13.000 1.1550 0.02533 0.01896 0.0392 +13.250 1.1687 0.02620 0.01989 0.0401 +13.500 1.1787 0.02736 0.02107 0.0412 +13.750 1.1847 0.02888 0.02257 0.0423 +14.000 1.1953 0.03012 0.02387 0.0430 +14.250 1.2052 0.03147 0.02526 0.0436 +14.500 1.2111 0.03319 0.02698 0.0443 +14.750 1.2153 0.03510 0.02891 0.0449 +15.000 1.2252 0.03660 0.03049 0.0452 +15.250 1.2315 0.03847 0.03238 0.0454 +15.500 1.2333 0.04078 0.03471 0.0456 +15.750 1.2364 0.04305 0.03702 0.0457 +16.000 1.2429 0.04507 0.03912 0.0457 +16.250 1.2463 0.04742 0.04151 0.0456 +16.500 1.2460 0.05018 0.04430 0.0453 +16.750 1.2446 0.05309 0.04724 0.0450 +17.000 1.2484 0.05558 0.04982 0.0446 +17.250 1.2499 0.05832 0.05263 0.0441 +17.500 1.2487 0.06139 0.05573 0.0435 +17.750 1.2439 0.06486 0.05921 0.0428 +18.000 1.2436 0.06794 0.06238 0.0420 +18.250 1.2437 0.07102 0.06554 0.0412 +18.500 1.2422 0.07429 0.06887 0.0402 +18.750 1.2382 0.07790 0.07251 0.0392 +19.000 1.2338 0.08146 0.07607 0.0382 +19.250 1.2320 0.08490 0.07961 0.0371 +20 0.985800000000000 0.282000000000000 0 +22 0.994000000000000 0.329000000000000 0 +25 1.03500000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 +! ------------------------------------------------------------------------------ +! data for table +! ------------------------------------------------------------------------------ +1.0 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +17.801185316865297 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-17.801185316865297 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.0573 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.0573 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0082 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +221 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -1.10180000000000 0.405000000000000 0 +-22 -1.06440000000000 0.329000000000000 0 +-20 -1.05540000000000 0.282000000000000 0 +-19.750 -1.3432 0.07827 0.07364 -0.0368 +-19.500 -1.3520 0.07412 0.06942 -0.0380 +-19.250 -1.3588 0.07026 0.06549 -0.0390 +-19.000 -1.3630 0.06671 0.06187 -0.0399 +-18.750 -1.3640 0.06359 0.05867 -0.0407 +-18.500 -1.3727 0.05963 0.05465 -0.0415 +-18.250 -1.3785 0.05608 0.05105 -0.0422 +-18.000 -1.3809 0.05296 0.04787 -0.0427 +-17.750 -1.3805 0.05018 0.04503 -0.0430 +-17.500 -1.3775 0.04772 0.04250 -0.0433 +-17.250 -1.3782 0.04492 0.03965 -0.0435 +-17.000 -1.3782 0.04225 0.03694 -0.0436 +-16.750 -1.3750 0.03997 0.03462 -0.0436 +-16.500 -1.3687 0.03803 0.03263 -0.0435 +-16.250 -1.3613 0.03623 0.03077 -0.0433 +-16.000 -1.3583 0.03408 0.02860 -0.0429 +-15.750 -1.3521 0.03228 0.02677 -0.0425 +-15.500 -1.3428 0.03079 0.02525 -0.0420 +-15.250 -1.3326 0.02943 0.02384 -0.0415 +-15.000 -1.3257 0.02784 0.02225 -0.0407 +-14.750 -1.3161 0.02652 0.02091 -0.0399 +-14.500 -1.3036 0.02546 0.01981 -0.0392 +-14.250 -1.2929 0.02431 0.01864 -0.0383 +-14.000 -1.2826 0.02319 0.01751 -0.0372 +-13.750 -1.2700 0.02226 0.01657 -0.0361 +-13.500 -1.2556 0.02150 0.01577 -0.0351 +-13.250 -1.2456 0.02055 0.01483 -0.0335 +-13.000 -1.2336 0.01979 0.01407 -0.0319 +-12.750 -1.2204 0.01920 0.01346 -0.0303 +-12.500 -1.2131 0.01851 0.01277 -0.0277 +-12.250 -1.2076 0.01796 0.01222 -0.0245 +-12.000 -1.2041 0.01754 0.01179 -0.0208 +-11.750 -1.2064 0.01719 0.01142 -0.0159 +-11.500 -1.1882 0.01662 0.01088 -0.0150 +-11.250 -1.1585 0.01613 0.01039 -0.0162 +-11.000 -1.1294 0.01557 0.00986 -0.0173 +-10.750 -1.0982 0.01510 0.00941 -0.0186 +-10.500 -1.0669 0.01459 0.00894 -0.0201 +-10.250 -1.0385 0.01417 0.00853 -0.0207 +-10.000 -1.0087 0.01368 0.00809 -0.0217 +-9.750 -0.9774 0.01330 0.00772 -0.0228 +-9.500 -0.9478 0.01283 0.00731 -0.0237 +-9.250 -0.9247 0.01253 0.00701 -0.0229 +-9.000 -0.9015 0.01212 0.00664 -0.0222 +-8.750 -0.8817 0.01186 0.00638 -0.0207 +-8.500 -0.8619 0.01154 0.00607 -0.0192 +-8.250 -0.8432 0.01131 0.00585 -0.0174 +-8.000 -0.8229 0.01107 0.00561 -0.0159 +-7.750 -0.8009 0.01083 0.00538 -0.0147 +-7.500 -0.7780 0.01061 0.00516 -0.0137 +-7.250 -0.7551 0.01040 0.00495 -0.0128 +-7.000 -0.7311 0.01020 0.00476 -0.0120 +-6.750 -0.7074 0.01001 0.00456 -0.0111 +-6.500 -0.6827 0.00983 0.00438 -0.0105 +-6.250 -0.6583 0.00966 0.00420 -0.0098 +-6.000 -0.6331 0.00950 0.00405 -0.0092 +-5.750 -0.6081 0.00935 0.00389 -0.0086 +-5.500 -0.5827 0.00922 0.00375 -0.0080 +-5.250 -0.5571 0.00908 0.00361 -0.0075 +-5.000 -0.5317 0.00897 0.00348 -0.0070 +-4.750 -0.5056 0.00885 0.00336 -0.0065 +-4.500 -0.4799 0.00874 0.00324 -0.0061 +-4.250 -0.4538 0.00866 0.00314 -0.0056 +-4.000 -0.4278 0.00855 0.00304 -0.0052 +-3.750 -0.4013 0.00849 0.00296 -0.0048 +-3.500 -0.3754 0.00839 0.00286 -0.0044 +-3.250 -0.3483 0.00835 0.00280 -0.0041 +-3.000 -0.3226 0.00827 0.00272 -0.0036 +-2.500 -0.2691 0.00816 0.00260 -0.0029 +-2.250 -0.2421 0.00814 0.00255 -0.0027 +-2.000 -0.2155 0.00807 0.00250 -0.0023 +-1.750 -0.1886 0.00807 0.00246 -0.0020 +-1.500 -0.1618 0.00801 0.00242 -0.0017 +-1.250 -0.1347 0.00800 0.00240 -0.0015 +-1.000 -0.1080 0.00798 0.00237 -0.0011 +-0.750 -0.0808 0.00796 0.00235 -0.0009 +-0.250 -0.0269 0.00793 0.00233 -0.0003 +0.000 0.0000 0.00796 0.00233 0.0000 +0.250 0.0269 0.00793 0.00233 0.0003 +0.750 0.0808 0.00796 0.00235 0.0009 +1.000 0.1080 0.00798 0.00237 0.0011 +1.250 0.1347 0.00800 0.00240 0.0015 +1.500 0.1618 0.00801 0.00242 0.0017 +1.750 0.1886 0.00807 0.00246 0.0020 +2.000 0.2155 0.00807 0.00250 0.0023 +2.250 0.2421 0.00814 0.00255 0.0027 +2.500 0.2692 0.00816 0.00260 0.0029 +3.000 0.3227 0.00827 0.00272 0.0036 +3.250 0.3483 0.00835 0.00280 0.0041 +3.500 0.3754 0.00839 0.00286 0.0043 +3.750 0.4014 0.00849 0.00296 0.0048 +4.000 0.4279 0.00855 0.00304 0.0052 +4.250 0.4539 0.00866 0.00314 0.0056 +4.500 0.4800 0.00874 0.00324 0.0060 +4.750 0.5058 0.00885 0.00336 0.0065 +5.000 0.5318 0.00897 0.00348 0.0069 +5.250 0.5573 0.00908 0.00361 0.0075 +5.500 0.5829 0.00922 0.00375 0.0080 +5.750 0.6083 0.00935 0.00389 0.0085 +6.000 0.6333 0.00950 0.00405 0.0091 +6.250 0.6585 0.00966 0.00420 0.0097 +6.500 0.6829 0.00983 0.00438 0.0104 +6.750 0.7076 0.01001 0.00456 0.0111 +7.000 0.7314 0.01020 0.00476 0.0119 +7.250 0.7554 0.01040 0.00495 0.0127 +7.500 0.7784 0.01061 0.00516 0.0137 +7.750 0.8013 0.01083 0.00538 0.0146 +8.000 0.8233 0.01107 0.00561 0.0158 +8.250 0.8438 0.01131 0.00585 0.0172 +8.500 0.8625 0.01154 0.00607 0.0191 +8.750 0.8823 0.01186 0.00638 0.0206 +9.000 0.9021 0.01212 0.00664 0.0221 +9.250 0.9253 0.01252 0.00700 0.0228 +9.500 0.9483 0.01283 0.00730 0.0236 +9.750 0.9780 0.01329 0.00772 0.0227 +10.000 1.0093 0.01368 0.00808 0.0216 +10.250 1.0390 0.01416 0.00853 0.0206 +10.500 1.0676 0.01458 0.00893 0.0199 +10.750 1.0990 0.01510 0.00940 0.0185 +11.000 1.1302 0.01556 0.00985 0.0171 +11.250 1.1594 0.01612 0.01038 0.0160 +11.500 1.1891 0.01661 0.01086 0.0149 +11.750 1.2063 0.01717 0.01140 0.0159 +12.000 1.2043 0.01752 0.01177 0.0208 +12.250 1.2080 0.01794 0.01220 0.0245 +12.500 1.2137 0.01849 0.01275 0.0276 +12.750 1.2213 0.01918 0.01343 0.0302 +13.000 1.2347 0.01977 0.01405 0.0318 +13.250 1.2468 0.02053 0.01481 0.0333 +13.500 1.2570 0.02148 0.01575 0.0348 +13.750 1.2716 0.02223 0.01654 0.0358 +14.000 1.2842 0.02316 0.01748 0.0369 +14.250 1.2946 0.02428 0.01861 0.0380 +14.500 1.3057 0.02541 0.01976 0.0389 +14.750 1.3182 0.02648 0.02086 0.0396 +15.000 1.3279 0.02780 0.02220 0.0404 +15.250 1.3347 0.02939 0.02380 0.0412 +15.500 1.3454 0.03072 0.02518 0.0417 +15.750 1.3546 0.03222 0.02671 0.0421 +16.000 1.3609 0.03402 0.02854 0.0425 +16.250 1.3639 0.03617 0.03071 0.0429 +16.500 1.3719 0.03793 0.03253 0.0431 +16.750 1.3781 0.03987 0.03452 0.0432 +17.000 1.3814 0.04216 0.03685 0.0432 +17.250 1.3813 0.04484 0.03957 0.0431 +17.500 1.3813 0.04758 0.04236 0.0429 +17.750 1.3843 0.05004 0.04489 0.0426 +18.000 1.3848 0.05282 0.04773 0.0422 +18.250 1.3824 0.05595 0.05091 0.0417 +18.500 1.3766 0.05951 0.05452 0.0410 +18.750 1.3688 0.06336 0.05844 0.0402 +19.000 1.3675 0.06653 0.06168 0.0394 +19.250 1.3631 0.07010 0.06533 0.0385 +20 1.05540000000000 0.282000000000000 0 +22 1.06440000000000 0.329000000000000 0 +25 1.10180000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 +! ------------------------------------------------------------------------------ +! data for table +! ------------------------------------------------------------------------------ +2.0 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +20.027374578257152 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-20.027374578257152 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.151 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.151 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0077 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +105 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +-1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 +-1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 +-1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 +-1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 +-1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 +-1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 +-1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 +-1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 +-1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 +-1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 +-1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 +-1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 +-1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 +-1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 +-1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 +-1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 +-9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 +-9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 +-8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 +-8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 +-7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 +-7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 +-6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 +-6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 +-5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 +-5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 +-4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 +-4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 +-3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 +-3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 +-2.50000000e+01 -1.14680000e+00 4.05000000e-01 0.00000000e+00 +-2.20000000e+01 -1.11270000e+00 3.29000000e-01 0.00000000e+00 +-2.00000000e+01 -1.11720000e+00 2.82000000e-01 0.00000000e+00 +-1.80000000e+01 -1.13830000e+00 2.38000000e-01 0.00000000e+00 +-1.70000000e+01 -1.15500000e+00 1.20000000e-01 0.00000000e+00 +-1.60000000e+01 -1.16950000e+00 2.40000000e-02 0.00000000e+00 +-1.50000000e+01 -1.18130000e+00 2.18000000e-02 0.00000000e+00 +-1.40000000e+01 -1.18130000e+00 1.97000000e-02 0.00000000e+00 +-1.30000000e+01 -1.16620000e+00 1.79000000e-02 0.00000000e+00 +-1.20000000e+01 -1.12960000e+00 1.63000000e-02 0.00000000e+00 +-1.10000000e+01 -1.07720000e+00 1.48000000e-02 0.00000000e+00 +-1.00000000e+01 -1.01110000e+00 1.34000000e-02 0.00000000e+00 +-9.00000000e+00 -9.31400000e-01 1.22000000e-02 0.00000000e+00 +-8.00000000e+00 -8.43900000e-01 1.11000000e-02 0.00000000e+00 +-7.00000000e+00 -7.44900000e-01 1.01000000e-02 0.00000000e+00 +-6.00000000e+00 -6.60000000e-01 9.30000000e-03 0.00000000e+00 +-5.00000000e+00 -5.50000000e-01 8.70000000e-03 0.00000000e+00 +-4.00000000e+00 -4.40000000e-01 8.40000000e-03 0.00000000e+00 +-3.00000000e+00 -3.30000000e-01 8.00000000e-03 0.00000000e+00 +-2.00000000e+00 -2.20000000e-01 7.80000000e-03 0.00000000e+00 +-1.00000000e+00 -1.10000000e-01 7.70000000e-03 0.00000000e+00 + 0.00000000e+00 0.00000000e+00 7.70000000e-03 0.00000000e+00 + 1.00000000e+00 1.10000000e-01 7.70000000e-03 0.00000000e+00 + 2.00000000e+00 2.20000000e-01 7.80000000e-03 0.00000000e+00 + 3.00000000e+00 3.30000000e-01 8.00000000e-03 0.00000000e+00 + 4.00000000e+00 4.40000000e-01 8.40000000e-03 0.00000000e+00 + 5.00000000e+00 5.50000000e-01 8.70000000e-03 0.00000000e+00 + 6.00000000e+00 6.60000000e-01 9.30000000e-03 0.00000000e+00 + 7.00000000e+00 7.44900000e-01 1.01000000e-02 0.00000000e+00 + 8.00000000e+00 8.43900000e-01 1.11000000e-02 0.00000000e+00 + 9.00000000e+00 9.31400000e-01 1.22000000e-02 0.00000000e+00 + 1.00000000e+01 1.01110000e+00 1.34000000e-02 0.00000000e+00 + 1.10000000e+01 1.07720000e+00 1.48000000e-02 0.00000000e+00 + 1.20000000e+01 1.12960000e+00 1.63000000e-02 0.00000000e+00 + 1.30000000e+01 1.16620000e+00 1.79000000e-02 0.00000000e+00 + 1.40000000e+01 1.18130000e+00 1.97000000e-02 0.00000000e+00 + 1.50000000e+01 1.18130000e+00 2.18000000e-02 0.00000000e+00 + 1.60000000e+01 1.16950000e+00 2.40000000e-02 0.00000000e+00 + 1.70000000e+01 1.15500000e+00 1.20000000e-01 0.00000000e+00 + 1.80000000e+01 1.13830000e+00 2.38000000e-01 0.00000000e+00 + 2.00000000e+01 1.11720000e+00 2.82000000e-01 0.00000000e+00 + 2.20000000e+01 1.11270000e+00 3.29000000e-01 0.00000000e+00 + 2.50000000e+01 1.14680000e+00 4.05000000e-01 0.00000000e+00 + 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 + 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 + 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 + 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 + 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 + 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 + 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 + 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 + 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 + 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 + 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 + 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 + 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 + 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 + 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 + 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 + 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 + 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 + 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 + 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 + 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 + 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 + 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 + 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 + 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 + 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 + 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 + 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 + 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 + 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 + 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +! ------------------------------------------------------------------------------ +! data for table +! ------------------------------------------------------------------------------ +5.0 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +23.403123375221707 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-23.403123375221707 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.2617 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.2617 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0073 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +107 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +-1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 +-1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 +-1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 +-1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 +-1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 +-1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 +-1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 +-1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 +-1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 +-1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 +-1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 +-1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 +-1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 +-1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 +-1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 +-1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 +-9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 +-9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 +-8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 +-8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 +-7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 +-7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 +-6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 +-6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 +-5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 +-5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 +-4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 +-4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 +-3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 +-3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 +-2.50000000e+01 -1.29250000e+00 4.05000000e-01 0.00000000e+00 +-2.20000000e+01 -1.27140000e+00 3.29000000e-01 0.00000000e+00 +-2.00000000e+01 -1.27680000e+00 2.82000000e-01 0.00000000e+00 +-1.90000000e+01 -1.28530000e+00 1.40000000e-01 0.00000000e+00 +-1.80000000e+01 -1.29600000e+00 2.44000000e-02 0.00000000e+00 +-1.70000000e+01 -1.30380000e+00 2.23000000e-02 0.00000000e+00 +-1.60000000e+01 -1.30670000e+00 2.03000000e-02 0.00000000e+00 +-1.50000000e+01 -1.30040000e+00 1.85000000e-02 0.00000000e+00 +-1.40000000e+01 -1.28080000e+00 1.68000000e-02 0.00000000e+00 +-1.30000000e+01 -1.24300000e+00 1.53000000e-02 0.00000000e+00 +-1.20000000e+01 -1.18840000e+00 1.40000000e-02 0.00000000e+00 +-1.10000000e+01 -1.12110000e+00 1.28000000e-02 0.00000000e+00 +-1.00000000e+01 -1.04040000e+00 1.17000000e-02 0.00000000e+00 +-9.00000000e+00 -9.52500000e-01 1.08000000e-02 0.00000000e+00 +-8.00000000e+00 -8.53800000e-01 1.00000000e-02 0.00000000e+00 +-7.00000000e+00 -7.70000000e-01 9.30000000e-03 0.00000000e+00 +-6.00000000e+00 -6.60000000e-01 8.70000000e-03 0.00000000e+00 +-5.00000000e+00 -5.50000000e-01 8.30000000e-03 0.00000000e+00 +-4.00000000e+00 -4.40000000e-01 7.90000000e-03 0.00000000e+00 +-3.00000000e+00 -3.30000000e-01 7.70000000e-03 0.00000000e+00 +-2.00000000e+00 -2.20000000e-01 7.50000000e-03 0.00000000e+00 +-1.00000000e+00 -1.10000000e-01 7.30000000e-03 0.00000000e+00 + 0.00000000e+00 0.00000000e+00 7.30000000e-03 0.00000000e+00 + 1.00000000e+00 1.10000000e-01 7.30000000e-03 0.00000000e+00 + 2.00000000e+00 2.20000000e-01 7.50000000e-03 0.00000000e+00 + 3.00000000e+00 3.30000000e-01 7.70000000e-03 0.00000000e+00 + 4.00000000e+00 4.40000000e-01 7.90000000e-03 0.00000000e+00 + 5.00000000e+00 5.50000000e-01 8.30000000e-03 0.00000000e+00 + 6.00000000e+00 6.60000000e-01 8.70000000e-03 0.00000000e+00 + 7.00000000e+00 7.70000000e-01 9.30000000e-03 0.00000000e+00 + 8.00000000e+00 8.53800000e-01 1.00000000e-02 0.00000000e+00 + 9.00000000e+00 9.52500000e-01 1.08000000e-02 0.00000000e+00 + 1.00000000e+01 1.04040000e+00 1.17000000e-02 0.00000000e+00 + 1.10000000e+01 1.12110000e+00 1.28000000e-02 0.00000000e+00 + 1.20000000e+01 1.18840000e+00 1.40000000e-02 0.00000000e+00 + 1.30000000e+01 1.24300000e+00 1.53000000e-02 0.00000000e+00 + 1.40000000e+01 1.28080000e+00 1.68000000e-02 0.00000000e+00 + 1.50000000e+01 1.30040000e+00 1.85000000e-02 0.00000000e+00 + 1.60000000e+01 1.30670000e+00 2.03000000e-02 0.00000000e+00 + 1.70000000e+01 1.30380000e+00 2.23000000e-02 0.00000000e+00 + 1.80000000e+01 1.29600000e+00 2.44000000e-02 0.00000000e+00 + 1.90000000e+01 1.28530000e+00 1.40000000e-01 0.00000000e+00 + 2.00000000e+01 1.27680000e+00 2.82000000e-01 0.00000000e+00 + 2.20000000e+01 1.27140000e+00 3.29000000e-01 0.00000000e+00 + 2.50000000e+01 1.29250000e+00 4.05000000e-01 0.00000000e+00 + 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 + 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 + 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 + 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 + 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 + 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 + 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 + 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 + 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 + 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 + 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 + 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 + 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 + 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 + 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 + 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 + 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 + 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 + 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 + 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 + 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 + 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 + 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 + 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 + 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 + 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 + 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 + 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 + 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 + 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 + 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 + diff --git a/examples/literate/airfoils/NACA_0021_AD.txt b/examples/literate/airfoils/NACA_0021_AD.txt new file mode 100644 index 00000000..9766f4ee --- /dev/null +++ b/examples/literate/airfoils/NACA_0021_AD.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.277853 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 8.64E-03 + 9.89671379974747e-01 6.44E-03 + 9.64477131182153e-01 2.90E-03 + 9.39158624174899e-01 1.76E-03 + 9.13813162279310e-01 3.23E-03 + 8.88553591831403e-01 3.12E-03 + 8.63480304357990e-01 1.46E-03 + 8.38670008821752e-01 -1.52E-03 + 8.14184038980280e-01 -5.69E-03 + 7.90073507481042e-01 -1.10E-02 + 7.66396243180071e-01 -1.74E-02 + 7.43171762127060e-01 -2.47E-02 + 7.20393063763985e-01 -3.26E-02 + 6.98115514389012e-01 -4.11E-02 + 6.76338951051125e-01 -5.00E-02 + 6.54963698148296e-01 -5.91E-02 + 6.33966484340103e-01 -6.82E-02 + 6.13322712460925e-01 -7.73E-02 + 5.93009124541476e-01 -8.62E-02 + 5.73007900047194e-01 -9.49E-02 + 5.53307401144792e-01 -1.03E-01 + 5.33898576587071e-01 -1.11E-01 + 5.14779223154629e-01 -1.18E-01 + 4.95954396665602e-01 -1.25E-01 + 4.77430350386696e-01 -1.31E-01 + 4.59214886856257e-01 -1.37E-01 + 4.41321190252217e-01 -1.42E-01 + 4.23765543793179e-01 -1.46E-01 + 4.06561760993008e-01 -1.50E-01 + 3.89721882904375e-01 -1.53E-01 + 3.73261236217240e-01 -1.56E-01 + 3.57188855965126e-01 -1.58E-01 + 3.41516689450044e-01 -1.60E-01 + 3.26253343070801e-01 -1.61E-01 + 3.11407100100747e-01 -1.62E-01 + 2.96983147380361e-01 -1.62E-01 + 2.82986150094719e-01 -1.62E-01 + 2.69419666676137e-01 -1.62E-01 + 2.56284310763483e-01 -1.61E-01 + 2.43581181695766e-01 -1.60E-01 + 2.31309755891564e-01 -1.59E-01 + 2.19467527384275e-01 -1.57E-01 + 2.08052199943945e-01 -1.55E-01 + 1.97060878905940e-01 -1.53E-01 + 1.86487605109370e-01 -1.50E-01 + 1.76328427331090e-01 -1.48E-01 + 1.66576425927345e-01 -1.45E-01 + 1.57224710042703e-01 -1.42E-01 + 1.48263768632238e-01 -1.39E-01 + 1.39686465720747e-01 -1.35E-01 + 1.31484076933721e-01 -1.32E-01 + 1.23644002494218e-01 -1.29E-01 + 1.16158389148626e-01 -1.25E-01 + 1.09017608460481e-01 -1.22E-01 + 1.02208845279057e-01 -1.18E-01 + 9.57204441656418e-02 -1.14E-01 + 8.95431256675966e-02 -1.11E-01 + 8.36654273586364e-02 -1.07E-01 + 7.80736545281131e-02 -1.04E-01 + 7.27609142941316e-02 -9.99E-02 + 6.77181375640349e-02 -9.64E-02 + 6.29314267915325e-02 -9.28E-02 + 5.83918736326263e-02 -8.93E-02 + 5.40924087603125e-02 -8.58E-02 + 5.00238126094804e-02 -8.24E-02 + 4.61744194566202e-02 -7.90E-02 + 4.25343792761530e-02 -7.57E-02 + 3.90962763038171e-02 -7.24E-02 + 3.58516054447007e-02 -6.92E-02 + 3.27924500315299e-02 -6.61E-02 + 2.99188717479619e-02 -6.29E-02 + 2.72190044082920e-02 -5.99E-02 + 2.46896838543740e-02 -5.69E-02 + 2.23254525385638e-02 -5.40E-02 + 2.01130198509196e-02 -5.11E-02 + 1.80527586585474e-02 -4.83E-02 + 1.61356703170338e-02 -4.56E-02 + 1.43526037214418e-02 -4.29E-02 + 1.26925112458821e-02 -4.03E-02 + 1.11706366374529e-02 -3.77E-02 + 9.77352700565712e-03 -3.52E-02 + 8.49040361517659e-03 -3.28E-02 + 7.31269112385052e-03 -3.04E-02 + 6.25433551768215e-03 -2.81E-02 + 5.30829698548717e-03 -2.59E-02 + 4.45476327462913e-03 -2.37E-02 + 3.64530110445795e-03 -2.16E-02 + 2.91174185051685e-03 -1.96E-02 + 2.31718348065112e-03 -1.76E-02 + 1.82941121798937e-03 -1.57E-02 + 1.42352546318114e-03 -1.38E-02 + 1.12283938796851e-03 -1.20E-02 + 8.95185703762229e-04 -1.03E-02 + 7.19623688087765e-04 -8.62E-03 + 5.77020939120505e-04 -7.02E-03 + 4.52369924559997e-04 -5.49E-03 + 3.33108736652917e-04 -4.02E-03 + 2.19678789799849e-04 -2.62E-03 + 1.10470627512087e-04 -1.28E-03 + 0.00000000000000e+00 0.00E+00 + 1.02143597426640e-04 1.28E-03 + 2.01309614692119e-04 8.63E-03 + 2.99835334696142e-04 8.63E-03 + 4.01625134276334e-04 8.63E-03 + 5.03744497735996e-04 8.63E-03 + 6.18346425662303e-04 8.63E-03 + 7.62162373651962e-04 8.63E-03 + 9.44028461513286e-04 8.63E-03 + 1.18336819581177e-03 8.63E-03 + 1.50884511188477e-03 8.63E-03 + 1.89788727592515e-03 8.63E-03 + 2.36899110997143e-03 8.63E-03 + 2.93906777320867e-03 8.63E-03 + 3.59867586435142e-03 8.63E-03 + 4.30670940618765e-03 8.63E-03 + 5.09720271325558e-03 8.63E-03 + 5.99752167084764e-03 8.63E-03 + 7.00809148016107e-03 8.63E-03 + 8.11991886289441e-03 8.63E-03 + 9.32294853441525e-03 8.63E-03 + 1.06452748433505e-02 8.63E-03 + 1.20919016758476e-02 8.63E-03 + 1.36657091050637e-02 8.63E-03 + 1.53619984984854e-02 8.63E-03 + 1.71997879098679e-02 8.63E-03 + 1.91847655820185e-02 8.63E-03 + 2.13253359844419e-02 8.63E-03 + 2.36315005758345e-02 8.63E-03 + 2.61083491713133e-02 8.63E-03 + 2.87612971194336e-02 8.63E-03 + 3.15981507017924e-02 8.63E-03 + 3.46280735398022e-02 8.63E-03 + 3.78535969542887e-02 8.63E-03 + 4.12850297637147e-02 8.63E-03 + 4.49307842744234e-02 8.63E-03 + 4.87981987096494e-02 8.63E-03 + 5.28961002593181e-02 8.63E-03 + 5.72308802904099e-02 8.63E-03 + 6.18143169001669e-02 8.63E-03 + 6.66558158361478e-02 8.63E-03 + 7.17628435388181e-02 8.63E-03 + 7.71433685208692e-02 8.63E-03 + 8.28066597109082e-02 8.63E-03 + 8.87623370313537e-02 8.63E-03 + 9.50225498149768e-02 8.63E-03 + 1.01593365906552e-01 8.63E-03 + 1.08484689743345e-01 8.63E-03 + 1.15707532058366e-01 8.63E-03 + 1.23267869284954e-01 8.63E-03 + 1.31175086465833e-01 8.63E-03 + 1.39439557403268e-01 8.63E-03 + 1.48067257045342e-01 8.63E-03 + 1.57063639519303e-01 8.63E-03 + 1.66438358327925e-01 8.63E-03 + 1.76196693213626e-01 8.63E-03 + 1.86343854246133e-01 8.63E-03 + 1.96885647258938e-01 8.63E-03 + 2.07825319991041e-01 8.63E-03 + 2.19166830204027e-01 8.63E-03 + 2.30911494004837e-01 8.63E-03 + 2.43061659957463e-01 8.63E-03 + 2.55619522433114e-01 8.63E-03 + 2.68586808602858e-01 8.63E-03 + 2.81964767633922e-01 8.63E-03 + 2.95753029530419e-01 8.63E-03 + 3.09951274377490e-01 8.63E-03 + 3.24559071166843e-01 8.63E-03 + 3.39576055104730e-01 8.63E-03 + 3.55000214209568e-01 8.63E-03 + 3.70830022781953e-01 8.63E-03 + 3.87063242925100e-01 8.63E-03 + 4.03697484944282e-01 8.63E-03 + 4.20727347071592e-01 8.63E-03 + 4.38151752431921e-01 8.63E-03 + 4.55964245711291e-01 8.63E-03 + 4.74161067405196e-01 8.63E-03 + 4.92733472564726e-01 8.63E-03 + 5.11676517362321e-01 8.63E-03 + 5.30985351170107e-01 8.63E-03 + 5.50653338799897e-01 8.63E-03 + 5.70668704030238e-01 8.63E-03 + 5.91022299396154e-01 8.63E-03 + 6.11704971014609e-01 8.63E-03 + 6.32703405878887e-01 8.63E-03 + 6.54007799159681e-01 8.63E-03 + 6.75603313526683e-01 8.63E-03 + 6.97479344035197e-01 8.63E-03 + 7.19619100665882e-01 8.63E-03 + 7.42007863814197e-01 8.63E-03 + 7.64633916307294e-01 8.63E-03 + 7.87480347506928e-01 8.63E-03 + 8.10530974553361e-01 8.63E-03 + 8.33766686857151e-01 8.63E-03 + 8.57171368568559e-01 8.63E-03 + 8.80727606307419e-01 8.63E-03 + 9.04416064906437e-01 8.63E-03 + 9.28217017828997e-01 8.63E-03 + 9.52108466170963e-01 8.63E-03 + 9.76048832000119e-01 8.63E-03 + 1.00000000000000e+00 8.63E-03 diff --git a/examples/literate/airfoils/NACA_0021_DMS.csv b/examples/literate/airfoils/NACA_0021_DMS.csv new file mode 100644 index 00000000..2e840158 --- /dev/null +++ b/examples/literate/airfoils/NACA_0021_DMS.csv @@ -0,0 +1,34 @@ +100,0.0 +95,-1.412 +90,-2.534 +80,-4.591 +70,-6.412 +60,-7.986 +50,-9.265 +40,-10.156 +30,-10.504 +25,-10.397 +20,-10.04 +15,-9.354 +10,-8.195 +7.5,-7.35 +5,-6.221 +2.5,-4.576 +1.25,-3.315 +0,0 +1.25,3.315 +2.5,4.576 +5,6.221 +7.5,7.35 +10,8.195 +15,9.354 +20,10.04 +25,10.397 +30,10.504 +40,10.156 +50,9.265 +60,7.986 +70,6.412 +80,4.591 +90,2.534 +95,1.412 \ No newline at end of file diff --git a/examples/literate/airfoils/NACA_0021_DMS.dat b/examples/literate/airfoils/NACA_0021_DMS.dat new file mode 100644 index 00000000..47e03a15 --- /dev/null +++ b/examples/literate/airfoils/NACA_0021_DMS.dat @@ -0,0 +1,1402 @@ +Title: NACA0021 +Thickness to Chord Ratio: 0.21 +Zero Lift AOA (deg): 0.0 +Reverse Camber Direction: 0 + +Reynolds Number: 5e4 +BV Dyn. Stall Model - Positive Stall AOA (deg): 3.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -3.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 4.309 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 0.526 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -0.526 +AOA (deg) CL CD Cm25 +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -0.480200000000000 0.405000000000000 0 +-22 -0.334500000000000 0.329000000000000 0 +-20 -0.241400000000000 0.282000000000000 0 +-18 -0.161900000000000 0.238000000000000 0 +-16 -0.0981000000000000 0.196000000000000 0 +-14 -0.0833000000000000 0.158000000000000 0 +-12 -0.166000000000000 0.123000000000000 0 +-10.500 -0.3112 0.12560 0.11631 +-10.250 -0.2843 0.12215 0.11285 +-10.000 -0.3247 0.12282 0.11357 +-9.750 -0.2690 0.11676 0.10748 +-9.500 -0.2967 0.11674 0.10749 +-9.250 -0.2590 0.11173 0.10247 +-9.000 -0.2672 0.11069 0.10145 +-8.750 -0.3659 0.09402 0.08467 +-8.500 -0.3767 0.09022 0.08089 +-8.250 -0.4033 0.08534 0.07605 +-8.000 -0.4715 0.07745 0.06824 +-7.750 -0.4041 0.08041 0.07119 +-7.500 -0.4468 0.07517 0.06603 +-7.250 -0.6906 0.05799 0.04907 +-7.000 -0.8363 0.04920 0.04010 +-6.750 -0.7209 0.05447 0.04562 +-6.500 -0.8240 0.04776 0.03872 +-6.250 -0.7822 0.04914 0.04024 +-6.000 -0.8189 0.04596 0.03692 +-5.750 -0.7958 0.04632 0.03739 +-5.500 -0.8154 0.04402 0.03493 +-5.250 -0.7909 0.04456 0.03561 +-5.000 -0.8085 0.04222 0.03308 +-4.750 -0.7788 0.04326 0.03431 +-4.500 -0.7837 0.04171 0.03266 +-4.250 -0.7645 0.04213 0.03318 +-4.000 -0.7592 0.04136 0.03238 +-3.750 -0.7521 0.04079 0.03179 +-3.500 -0.7355 0.04107 0.03215 +-3.250 -0.7304 0.04029 0.03132 +-3.000 -0.6987 0.04088 0.03197 +-2.750 -0.6416 0.04215 0.03328 +-2.500 -0.5915 0.04298 0.03411 +-2.250 -0.5503 0.04341 0.03453 +-2.000 -0.5136 0.04365 0.03474 +-1.750 -0.4532 0.04526 0.03640 +-1.500 -0.3880 0.04646 0.03760 +-1.250 -0.3540 0.04667 0.03780 +-1.000 -0.3318 0.04665 0.03775 +-0.750 -0.2325 0.04876 0.03989 +-0.500 -0.1461 0.04940 0.04050 +-0.250 -0.1393 0.04928 0.04038 +0.000 0.0000 0.05040 0.04152 +0.250 0.1392 0.04928 0.04038 +0.500 0.1463 0.04939 0.04050 +0.750 0.2325 0.04876 0.03988 +1.000 0.3317 0.04665 0.03775 +1.250 0.3539 0.04667 0.03779 +1.500 0.3878 0.04646 0.03760 +1.750 0.4531 0.04526 0.03639 +2.000 0.5135 0.04365 0.03474 +2.250 0.5504 0.04340 0.03452 +2.500 0.5915 0.04297 0.03410 +2.750 0.6416 0.04214 0.03327 +3.000 0.6987 0.04087 0.03195 +3.250 0.7301 0.04029 0.03132 +3.500 0.7353 0.04106 0.03215 +3.750 0.7520 0.04077 0.03176 +4.000 0.7589 0.04135 0.03237 +4.250 0.7643 0.04211 0.03316 +4.500 0.7834 0.04171 0.03265 +4.750 0.7786 0.04325 0.03430 +5.000 0.8081 0.04222 0.03308 +5.250 0.7906 0.04455 0.03560 +5.500 0.8155 0.04398 0.03490 +5.750 0.7955 0.04631 0.03737 +6.000 0.8190 0.04593 0.03689 +6.250 0.7819 0.04913 0.04023 +6.500 0.8243 0.04773 0.03868 +6.750 0.7216 0.05441 0.04555 +7.000 0.6677 0.05811 0.04924 +7.250 0.6916 0.05791 0.04899 +7.500 0.4474 0.07510 0.06595 +7.750 0.4049 0.08033 0.07110 +8.000 0.4721 0.07739 0.06817 +8.250 0.4039 0.08528 0.07599 +8.500 0.3775 0.09015 0.08082 +8.750 0.3673 0.09391 0.08456 +9.000 0.3997 0.09451 0.08514 +9.250 0.3819 0.09944 0.09006 +9.500 0.3752 0.10386 0.09448 +9.750 0.3820 0.10800 0.09863 +10.250 0.2855 0.12214 0.11284 +10.500 0.3127 0.12563 0.11634 +12 0.166000000000000 0.123000000000000 0 +14 0.0833000000000000 0.158000000000000 0 +16 0.0981000000000000 0.196000000000000 0 +18 0.161900000000000 0.238000000000000 0 +20 0.241400000000000 0.282000000000000 0 +22 0.334500000000000 0.329000000000000 0 +25 0.480200000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 + +Reynolds Number: 1.0e5 +BV Dyn. Stall Model - Positive Stall AOA (deg): 5.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -5.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 5.371 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.031 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.031 +AOA (deg) CL CD Cm25 +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -0.666400000000000 0.405000000000000 0 +-22 -0.602300000000000 0.329000000000000 0 +-20 -0.592000000000000 0.282000000000000 0 +-18 -0.609800000000000 0.238000000000000 0 +-16.250 -0.5418 0.17959 0.17300 +-16.000 -0.5218 0.17458 0.16798 +-15.750 -1.0757 0.06945 0.06174 +-15.000 -1.0716 0.06221 0.05443 +-14.750 -1.1181 0.05655 0.04843 +-14.500 -1.1584 0.05230 0.04383 +-14.250 -1.1225 0.05198 0.04374 +-14.000 -1.1217 0.05028 0.04198 +-13.750 -1.1410 0.04769 0.03917 +-13.500 -1.1689 0.04524 0.03640 +-13.250 -1.1295 0.04478 0.03622 +-13.000 -1.1311 0.04343 0.03479 +-12.750 -1.1495 0.04176 0.03290 +-12.500 -1.1393 0.04058 0.03175 +-12.250 -1.1243 0.03993 0.03119 +-12.000 -1.1374 0.03889 0.03002 +-11.750 -1.1599 0.03782 0.02870 +-11.500 -1.1248 0.03722 0.02841 +-11.250 -1.1280 0.03641 0.02754 +-11.000 -1.1446 0.03548 0.02634 +-10.750 -1.1160 0.03489 0.02605 +-10.500 -1.1166 0.03422 0.02531 +-10.250 -1.1202 0.03336 0.02431 +-10.000 -1.1022 0.03292 0.02408 +-9.750 -1.1033 0.03226 0.02330 +-9.500 -1.0943 0.03159 0.02268 +-9.250 -1.0843 0.03117 0.02232 +-9.000 -1.0869 0.03049 0.02143 +-8.750 -1.0682 0.03009 0.02126 +-8.500 -1.0638 0.02958 0.02066 +-8.250 -1.0510 0.02910 0.02027 +-8.000 -1.0410 0.02874 0.01992 +-7.750 -1.0310 0.02826 0.01942 +-7.500 -1.0177 0.02799 0.01923 +-7.250 -1.0080 0.02755 0.01873 +-7.000 -0.9930 0.02735 0.01865 +-6.750 -0.9825 0.02698 0.01820 +-6.500 -0.9668 0.02682 0.01818 +-6.250 -0.9284 0.02666 0.01804 +-6.000 -0.8880 0.02654 0.01784 +-5.750 -0.8396 0.02658 0.01805 +-5.500 -0.8021 0.02640 0.01794 +-5.250 -0.7628 0.02623 0.01776 +-5.000 -0.7209 0.02613 0.01771 +-4.750 -0.6844 0.02600 0.01771 +-4.500 -0.6395 0.02580 0.01754 +-4.250 -0.6102 0.02564 0.01736 +-4.000 -0.5600 0.02548 0.01736 +-3.750 -0.5318 0.02530 0.01722 +-3.500 -0.4845 0.02500 0.01692 +-3.250 -0.4524 0.02493 0.01698 +-3.000 -0.4038 0.02461 0.01674 +-2.750 -0.3715 0.02434 0.01647 +-2.500 -0.3309 0.02410 0.01632 +-2.250 -0.2802 0.02367 0.01597 +-2.000 -0.2618 0.02352 0.01582 +-1.750 -0.2139 0.02312 0.01549 +-1.500 -0.1906 0.02308 0.01553 +-1.250 -0.1507 0.02259 0.01501 +-0.750 -0.0906 0.02245 0.01497 +-0.500 -0.0653 0.02229 0.01480 +-0.250 -0.0304 0.02238 0.01495 +0.000 0.0000 0.02216 0.01468 +0.250 0.0304 0.02238 0.01495 +0.500 0.0653 0.02229 0.01480 +0.750 0.0906 0.02245 0.01496 +1.250 0.1507 0.02260 0.01501 +1.500 0.1906 0.02308 0.01553 +1.750 0.2139 0.02312 0.01549 +2.000 0.2618 0.02352 0.01582 +2.250 0.2802 0.02366 0.01597 +2.500 0.3309 0.02410 0.01632 +2.750 0.3713 0.02434 0.01646 +3.000 0.4037 0.02461 0.01674 +3.250 0.4523 0.02492 0.01698 +3.500 0.4844 0.02500 0.01692 +3.750 0.5316 0.02530 0.01722 +4.000 0.5600 0.02548 0.01735 +4.250 0.6101 0.02563 0.01735 +4.500 0.6395 0.02580 0.01754 +4.750 0.6843 0.02599 0.01771 +5.000 0.7209 0.02612 0.01770 +5.250 0.7627 0.02622 0.01775 +5.500 0.8021 0.02639 0.01793 +5.750 0.8394 0.02657 0.01804 +6.000 0.8879 0.02653 0.01783 +6.250 0.9285 0.02665 0.01803 +6.500 0.9665 0.02681 0.01817 +6.750 0.9822 0.02697 0.01819 +7.000 0.9927 0.02734 0.01864 +7.250 1.0077 0.02754 0.01872 +7.500 1.0174 0.02798 0.01922 +7.750 1.0308 0.02825 0.01941 +8.000 1.0408 0.02873 0.01991 +8.250 1.0508 0.02909 0.02026 +8.500 1.0636 0.02957 0.02064 +8.750 1.0680 0.03008 0.02125 +9.000 1.0866 0.03048 0.02142 +9.250 1.0841 0.03116 0.02231 +9.500 1.0941 0.03159 0.02267 +9.750 1.1032 0.03225 0.02329 +10.000 1.1020 0.03291 0.02406 +10.250 1.1200 0.03335 0.02430 +10.500 1.1165 0.03421 0.02530 +10.750 1.1160 0.03488 0.02604 +11.000 1.1445 0.03547 0.02633 +11.250 1.1281 0.03640 0.02753 +11.500 1.1251 0.03721 0.02840 +11.750 1.1600 0.03781 0.02869 +12.000 1.1377 0.03888 0.03001 +12.250 1.1248 0.03992 0.03118 +12.500 1.1405 0.04056 0.03173 +12.750 1.1499 0.04176 0.03290 +13.000 1.1318 0.04342 0.03479 +13.250 1.1308 0.04476 0.03620 +13.500 1.1694 0.04524 0.03641 +13.750 1.1418 0.04770 0.03918 +14.000 1.1230 0.05026 0.04196 +14.250 1.1250 0.05190 0.04364 +14.500 1.1589 0.05233 0.04386 +14.750 1.1189 0.05658 0.04847 +15.000 1.0729 0.06222 0.05445 +15.250 0.5376 0.16648 0.15990 +16 0.648700000000000 0.196000000000000 0 +18 0.609800000000000 0.238000000000000 0 +20 0.592000000000000 0.282000000000000 0 +22 0.602300000000000 0.329000000000000 0 +25 0.666400000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 + +Reynolds Number: 2.0e5 +BV Dyn. Stall Model - Positive Stall AOA (deg): 5.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -5.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.32 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.32 +AOA (deg) CL CD Cm25 +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -0.886600000000000 0.405000000000000 0 +-22 -0.845300000000000 0.329000000000000 0 +-19.500 -1.1826 0.09047 0.08413 -0.0463 +-19.250 -1.2047 0.08434 0.07776 -0.0489 +-19.000 -1.2278 0.07832 0.07145 -0.0514 +-18.750 -1.2032 0.07853 0.07184 -0.0504 +-18.500 -1.1961 0.07650 0.06982 -0.0509 +-18.250 -1.1992 0.07318 0.06640 -0.0518 +-18.000 -1.2090 0.06910 0.06214 -0.0531 +-17.750 -1.2212 0.06488 0.05769 -0.0542 +-17.500 -1.2022 0.06431 0.05727 -0.0537 +-17.250 -1.1971 0.06218 0.05513 -0.0539 +-17.000 -1.1989 0.05930 0.05214 -0.0544 +-16.750 -1.2067 0.05590 0.04852 -0.0549 +-16.500 -1.1937 0.05462 0.04733 -0.0545 +-16.250 -1.1864 0.05287 0.04559 -0.0544 +-16.000 -1.1842 0.05064 0.04328 -0.0543 +-15.750 -1.1871 0.04802 0.04047 -0.0542 +-15.500 -1.1747 0.04673 0.03926 -0.0537 +-15.250 -1.1677 0.04512 0.03766 -0.0533 +-15.000 -1.1645 0.04322 0.03567 -0.0528 +-14.750 -1.1623 0.04128 0.03358 -0.0521 +-14.500 -1.1497 0.04012 0.03253 -0.0515 +-14.250 -1.1433 0.03864 0.03102 -0.0507 +-14.000 -1.1397 0.03701 0.02926 -0.0497 +-13.750 -1.1282 0.03582 0.02813 -0.0488 +-13.500 -1.1203 0.03459 0.02690 -0.0477 +-13.250 -1.1145 0.03330 0.02552 -0.0464 +-13.000 -1.1045 0.03217 0.02440 -0.0451 +-12.750 -1.0959 0.03114 0.02341 -0.0436 +-12.500 -1.0895 0.03011 0.02230 -0.0418 +-12.250 -1.0801 0.02915 0.02135 -0.0401 +-12.000 -1.0725 0.02831 0.02055 -0.0380 +-11.750 -1.0675 0.02752 0.01969 -0.0354 +-11.500 -1.0603 0.02674 0.01895 -0.0329 +-11.250 -1.0561 0.02610 0.01835 -0.0298 +-11.000 -1.0548 0.02555 0.01774 -0.0261 +-10.750 -1.0521 0.02497 0.01719 -0.0224 +-10.500 -1.0534 0.02452 0.01680 -0.0179 +-10.250 -1.0585 0.02419 0.01642 -0.0126 +-10.000 -1.0652 0.02387 0.01607 -0.0069 +-9.750 -1.0728 0.02355 0.01583 -0.0011 +-9.500 -1.0784 0.02330 0.01558 0.0045 +-9.250 -1.0798 0.02308 0.01526 0.0093 +-9.000 -1.0772 0.02265 0.01495 0.0132 +-8.750 -1.0743 0.02239 0.01469 0.0172 +-8.500 -1.0406 0.02193 0.01426 0.0153 +-8.250 -1.0014 0.02161 0.01391 0.0124 +-8.000 -0.9676 0.02111 0.01352 0.0106 +-7.750 -0.9285 0.02075 0.01314 0.0078 +-7.500 -0.8926 0.02036 0.01282 0.0057 +-7.250 -0.8568 0.01993 0.01244 0.0037 +-7.000 -0.8148 0.01961 0.01207 0.0006 +-6.750 -0.7844 0.01919 0.01179 -0.0002 +-6.500 -0.7448 0.01880 0.01142 -0.0027 +-6.250 -0.7005 0.01845 0.01107 -0.0062 +-6.000 -0.6726 0.01808 0.01081 -0.0063 +-5.750 -0.6312 0.01769 0.01043 -0.0090 +-5.500 -0.5890 0.01729 0.01007 -0.0118 +-5.250 -0.5649 0.01698 0.00984 -0.0110 +-5.000 -0.5284 0.01663 0.00944 -0.0125 +-4.750 -0.5013 0.01630 0.00924 -0.0121 +-4.500 -0.4704 0.01596 0.00889 -0.0124 +-4.250 -0.4429 0.01569 0.00867 -0.0120 +-4.000 -0.4151 0.01537 0.00839 -0.0117 +-3.750 -0.3892 0.01516 0.00815 -0.0109 +-3.500 -0.3617 0.01487 0.00794 -0.0104 +-3.250 -0.3370 0.01470 0.00772 -0.0095 +-3.000 -0.3091 0.01445 0.00752 -0.0090 +-2.750 -0.2848 0.01429 0.00737 -0.0080 +-2.500 -0.2571 0.01412 0.00718 -0.0075 +-2.250 -0.2326 0.01398 0.00709 -0.0066 +-2.000 -0.2073 0.01389 0.00694 -0.0057 +-1.750 -0.1801 0.01375 0.00684 -0.0052 +-1.500 -0.1557 0.01368 0.00675 -0.0043 +-1.250 -0.1288 0.01360 0.00668 -0.0037 +-1.000 -0.1032 0.01353 0.00661 -0.0029 +-0.750 -0.0783 0.01351 0.00657 -0.0020 +-0.250 -0.0264 0.01344 0.00651 -0.0006 +0.000 0.0000 0.01344 0.00652 0.0000 +0.250 0.0264 0.01344 0.00651 0.0006 +0.750 0.0783 0.01351 0.00657 0.0020 +1.000 0.1032 0.01353 0.00661 0.0029 +1.250 0.1288 0.01360 0.00668 0.0037 +1.500 0.1557 0.01368 0.00675 0.0043 +1.750 0.1801 0.01375 0.00684 0.0052 +2.000 0.2073 0.01389 0.00694 0.0057 +2.250 0.2326 0.01398 0.00709 0.0066 +2.500 0.2571 0.01412 0.00718 0.0075 +2.750 0.2848 0.01429 0.00737 0.0080 +3.000 0.3091 0.01444 0.00752 0.0090 +3.250 0.3371 0.01470 0.00772 0.0095 +3.500 0.3617 0.01486 0.00793 0.0104 +3.750 0.3893 0.01516 0.00815 0.0109 +4.000 0.4151 0.01537 0.00839 0.0116 +4.250 0.4429 0.01568 0.00866 0.0120 +4.500 0.4704 0.01595 0.00889 0.0124 +4.750 0.5013 0.01630 0.00924 0.0121 +5.000 0.5284 0.01663 0.00944 0.0125 +5.250 0.5649 0.01697 0.00983 0.0110 +5.500 0.5891 0.01728 0.01007 0.0118 +5.750 0.6313 0.01769 0.01042 0.0090 +6.000 0.6726 0.01808 0.01081 0.0063 +6.250 0.7006 0.01845 0.01106 0.0062 +6.500 0.7449 0.01880 0.01142 0.0027 +6.750 0.7845 0.01919 0.01178 0.0002 +7.000 0.8149 0.01961 0.01207 -0.0006 +7.250 0.8569 0.01992 0.01244 -0.0038 +7.500 0.8926 0.02035 0.01281 -0.0057 +7.750 0.9287 0.02074 0.01313 -0.0079 +8.000 0.9678 0.02110 0.01351 -0.0106 +8.250 1.0017 0.02160 0.01390 -0.0124 +8.500 1.0409 0.02192 0.01425 -0.0153 +8.750 1.0741 0.02238 0.01468 -0.0171 +9.000 1.0770 0.02264 0.01494 -0.0132 +9.250 1.0797 0.02306 0.01524 -0.0093 +9.500 1.0783 0.02329 0.01557 -0.0045 +9.750 1.0729 0.02354 0.01582 0.0010 +10.000 1.0653 0.02386 0.01606 0.0069 +10.250 1.0586 0.02418 0.01641 0.0126 +10.500 1.0536 0.02451 0.01678 0.0179 +10.750 1.0524 0.02495 0.01718 0.0223 +11.000 1.0551 0.02554 0.01772 0.0260 +11.250 1.0565 0.02609 0.01833 0.0297 +11.500 1.0607 0.02673 0.01893 0.0328 +11.750 1.0680 0.02750 0.01967 0.0354 +12.000 1.0731 0.02829 0.02053 0.0379 +12.250 1.0810 0.02913 0.02133 0.0400 +12.500 1.0904 0.03010 0.02228 0.0417 +12.750 1.0969 0.03112 0.02339 0.0435 +13.000 1.1057 0.03215 0.02438 0.0449 +13.250 1.1157 0.03329 0.02550 0.0462 +13.500 1.1216 0.03457 0.02688 0.0475 +13.750 1.1297 0.03580 0.02810 0.0486 +14.000 1.1411 0.03700 0.02924 0.0495 +14.250 1.1448 0.03862 0.03100 0.0505 +14.500 1.1515 0.04009 0.03250 0.0512 +14.750 1.1647 0.04122 0.03351 0.0519 +15.000 1.1663 0.04320 0.03565 0.0525 +15.250 1.1697 0.04508 0.03762 0.0530 +15.500 1.1770 0.04669 0.03921 0.0534 +15.750 1.1888 0.04802 0.04047 0.0539 +16.000 1.1862 0.05062 0.04326 0.0540 +16.250 1.1888 0.05282 0.04554 0.0541 +16.500 1.1965 0.05454 0.04724 0.0542 +16.750 1.2085 0.05592 0.04855 0.0545 +17.000 1.2012 0.05929 0.05213 0.0540 +17.250 1.1998 0.06212 0.05507 0.0536 +17.500 1.2054 0.06420 0.05716 0.0533 +17.750 1.2264 0.06458 0.05736 0.0540 +18.000 1.2113 0.06911 0.06215 0.0527 +18.250 1.2021 0.07314 0.06636 0.0514 +18.500 1.1994 0.07641 0.06972 0.0505 +18.750 1.2073 0.07835 0.07164 0.0501 +19.000 1.2296 0.07842 0.07155 0.0509 +19.250 1.2067 0.08443 0.07786 0.0485 +20 0.839700000000000 0.282000000000000 0 +22 0.845300000000000 0.329000000000000 0 +25 0.886600000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 + +Reynolds Number: 5e5 +BV Dyn. Stall Model - Positive Stall AOA (deg): 6.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -6.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.54 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.54 +AOA (deg) CL CD Cm25 +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -1.03500000000000 0.405000000000000 0 +-22 -0.994000000000000 0.329000000000000 0 +-20 -0.985800000000000 0.282000000000000 0 +-19.750 -1.2237 0.09201 0.08687 -0.0351 +-19.500 -1.2258 0.08851 0.08331 -0.0364 +-19.250 -1.2282 0.08499 0.07969 -0.0376 +-19.000 -1.2301 0.08156 0.07618 -0.0387 +-18.750 -1.2347 0.07798 0.07260 -0.0397 +-18.500 -1.2386 0.07438 0.06896 -0.0407 +-18.250 -1.2399 0.07113 0.06565 -0.0416 +-18.000 -1.2400 0.06805 0.06249 -0.0425 +-17.750 -1.2408 0.06492 0.05928 -0.0432 +-17.500 -1.2455 0.06147 0.05582 -0.0439 +-17.250 -1.2466 0.05841 0.05273 -0.0445 +-17.000 -1.2451 0.05568 0.04992 -0.0450 +-16.750 -1.2412 0.05321 0.04736 -0.0454 +-16.500 -1.2432 0.05024 0.04437 -0.0457 +-16.250 -1.2435 0.04749 0.04159 -0.0459 +-16.000 -1.2401 0.04515 0.03921 -0.0461 +-15.750 -1.2336 0.04313 0.03711 -0.0461 +-15.500 -1.2310 0.04083 0.03476 -0.0460 +-15.250 -1.2290 0.03853 0.03245 -0.0458 +-15.000 -1.2228 0.03667 0.03056 -0.0455 +-14.750 -1.2129 0.03516 0.02898 -0.0452 +-14.500 -1.2091 0.03322 0.02702 -0.0446 +-14.250 -1.2032 0.03152 0.02530 -0.0439 +-14.000 -1.1933 0.03017 0.02392 -0.0433 +-13.750 -1.1831 0.02890 0.02260 -0.0425 +-13.500 -1.1771 0.02739 0.02110 -0.0414 +-13.250 -1.1671 0.02624 0.01993 -0.0404 +-13.000 -1.1535 0.02537 0.01900 -0.0394 +-12.750 -1.1475 0.02410 0.01775 -0.0378 +-12.500 -1.1375 0.02317 0.01682 -0.0363 +-12.250 -1.1246 0.02250 0.01610 -0.0348 +-12.000 -1.1200 0.02154 0.01518 -0.0323 +-11.750 -1.1136 0.02086 0.01450 -0.0296 +-11.500 -1.1058 0.02039 0.01399 -0.0268 +-11.250 -1.1078 0.01975 0.01338 -0.0225 +-11.000 -1.1107 0.01929 0.01293 -0.0177 +-10.750 -1.1141 0.01898 0.01260 -0.0127 +-10.500 -1.1224 0.01870 0.01229 -0.0067 +-10.250 -1.0934 0.01806 0.01171 -0.0080 +-10.000 -1.0611 0.01758 0.01122 -0.0096 +-9.750 -1.0285 0.01705 0.01074 -0.0113 +-9.500 -0.9983 0.01656 0.01028 -0.0124 +-9.250 -0.9668 0.01609 0.00984 -0.0138 +-9.000 -0.9330 0.01561 0.00939 -0.0155 +-8.750 -0.8959 0.01519 0.00899 -0.0178 +-8.500 -0.8643 0.01471 0.00856 -0.0190 +-8.250 -0.8319 0.01436 0.00821 -0.0202 +-8.000 -0.8001 0.01385 0.00778 -0.0214 +-7.750 -0.7692 0.01351 0.00745 -0.0222 +-7.500 -0.7466 0.01314 0.00713 -0.0212 +-7.250 -0.7182 0.01282 0.00681 -0.0214 +-7.000 -0.6987 0.01251 0.00655 -0.0197 +-6.750 -0.6738 0.01225 0.00627 -0.0190 +-6.500 -0.6532 0.01198 0.00604 -0.0175 +-6.250 -0.6292 0.01176 0.00580 -0.0166 +-6.000 -0.6071 0.01151 0.00558 -0.0154 +-5.750 -0.5831 0.01132 0.00538 -0.0145 +-5.500 -0.5596 0.01110 0.00517 -0.0135 +-5.250 -0.5355 0.01093 0.00500 -0.0127 +-5.000 -0.5109 0.01076 0.00481 -0.0119 +-4.750 -0.4866 0.01060 0.00467 -0.0111 +-4.500 -0.4615 0.01047 0.00452 -0.0104 +-4.250 -0.4368 0.01033 0.00437 -0.0096 +-4.000 -0.4113 0.01023 0.00425 -0.0090 +-3.750 -0.3865 0.01010 0.00411 -0.0083 +-3.500 -0.3605 0.01003 0.00401 -0.0078 +-3.250 -0.3357 0.00991 0.00391 -0.0071 +-2.750 -0.2845 0.00976 0.00373 -0.0059 +-2.500 -0.2583 0.00972 0.00365 -0.0054 +-2.250 -0.2331 0.00965 0.00358 -0.0048 +-2.000 -0.2069 0.00960 0.00352 -0.0043 +-1.750 -0.1814 0.00956 0.00346 -0.0037 +-1.500 -0.1554 0.00952 0.00342 -0.0032 +-1.250 -0.1295 0.00949 0.00338 -0.0027 +-1.000 -0.1040 0.00947 0.00334 -0.0020 +-0.750 -0.0774 0.00946 0.00332 -0.0016 +-0.500 -0.0521 0.00943 0.00331 -0.0010 +-0.250 -0.0258 0.00944 0.00329 -0.0006 +0.000 0.0000 0.00942 0.00329 0.0000 +0.250 0.0258 0.00944 0.00329 0.0006 +0.500 0.0521 0.00943 0.00331 0.0010 +0.750 0.0774 0.00946 0.00332 0.0016 +1.000 0.1040 0.00947 0.00334 0.0020 +1.250 0.1295 0.00949 0.00338 0.0027 +1.500 0.1555 0.00952 0.00341 0.0032 +1.750 0.1815 0.00956 0.00346 0.0037 +2.000 0.2069 0.00960 0.00352 0.0043 +2.250 0.2331 0.00965 0.00358 0.0048 +2.500 0.2583 0.00972 0.00365 0.0054 +2.750 0.2845 0.00976 0.00373 0.0059 +3.250 0.3357 0.00991 0.00391 0.0071 +3.500 0.3606 0.01003 0.00401 0.0078 +3.750 0.3866 0.01010 0.00411 0.0083 +4.000 0.4114 0.01023 0.00425 0.0090 +4.250 0.4369 0.01033 0.00437 0.0096 +4.500 0.4616 0.01047 0.00452 0.0104 +4.750 0.4867 0.01060 0.00467 0.0111 +5.000 0.5110 0.01076 0.00481 0.0119 +5.250 0.5356 0.01093 0.00500 0.0127 +5.500 0.5598 0.01110 0.00517 0.0135 +5.750 0.5833 0.01132 0.00538 0.0145 +6.000 0.6073 0.01151 0.00558 0.0153 +6.250 0.6294 0.01176 0.00580 0.0166 +6.500 0.6535 0.01198 0.00604 0.0174 +6.750 0.6741 0.01225 0.00627 0.0189 +7.000 0.6990 0.01251 0.00655 0.0196 +7.250 0.7185 0.01282 0.00681 0.0213 +7.500 0.7469 0.01314 0.00712 0.0212 +7.750 0.7695 0.01351 0.00744 0.0221 +8.000 0.8005 0.01385 0.00778 0.0213 +8.250 0.8323 0.01435 0.00821 0.0201 +8.500 0.8646 0.01470 0.00856 0.0190 +8.750 0.8964 0.01519 0.00899 0.0177 +9.000 0.9335 0.01561 0.00939 0.0154 +9.250 0.9673 0.01609 0.00983 0.0136 +9.500 0.9988 0.01656 0.01027 0.0123 +9.750 1.0292 0.01704 0.01073 0.0112 +10.000 1.0618 0.01757 0.01121 0.0095 +10.250 1.0941 0.01805 0.01169 0.0078 +10.500 1.1224 0.01868 0.01227 0.0067 +10.750 1.1141 0.01897 0.01258 0.0127 +11.000 1.1108 0.01927 0.01291 0.0177 +11.250 1.1079 0.01973 0.01335 0.0225 +11.500 1.1062 0.02037 0.01396 0.0267 +11.750 1.1141 0.02084 0.01448 0.0295 +12.000 1.1207 0.02152 0.01515 0.0322 +12.250 1.1256 0.02247 0.01607 0.0346 +12.500 1.1386 0.02315 0.01680 0.0361 +12.750 1.1487 0.02408 0.01773 0.0376 +13.000 1.1550 0.02533 0.01896 0.0392 +13.250 1.1687 0.02620 0.01989 0.0401 +13.500 1.1787 0.02736 0.02107 0.0412 +13.750 1.1847 0.02888 0.02257 0.0423 +14.000 1.1953 0.03012 0.02387 0.0430 +14.250 1.2052 0.03147 0.02526 0.0436 +14.500 1.2111 0.03319 0.02698 0.0443 +14.750 1.2153 0.03510 0.02891 0.0449 +15.000 1.2252 0.03660 0.03049 0.0452 +15.250 1.2315 0.03847 0.03238 0.0454 +15.500 1.2333 0.04078 0.03471 0.0456 +15.750 1.2364 0.04305 0.03702 0.0457 +16.000 1.2429 0.04507 0.03912 0.0457 +16.250 1.2463 0.04742 0.04151 0.0456 +16.500 1.2460 0.05018 0.04430 0.0453 +16.750 1.2446 0.05309 0.04724 0.0450 +17.000 1.2484 0.05558 0.04982 0.0446 +17.250 1.2499 0.05832 0.05263 0.0441 +17.500 1.2487 0.06139 0.05573 0.0435 +17.750 1.2439 0.06486 0.05921 0.0428 +18.000 1.2436 0.06794 0.06238 0.0420 +18.250 1.2437 0.07102 0.06554 0.0412 +18.500 1.2422 0.07429 0.06887 0.0402 +18.750 1.2382 0.07790 0.07251 0.0392 +19.000 1.2338 0.08146 0.07607 0.0382 +19.250 1.2320 0.08490 0.07961 0.0371 +20 0.985800000000000 0.282000000000000 0 +22 0.994000000000000 0.329000000000000 0 +25 1.03500000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 + +Reynolds Number: 1e6 +BV Dyn. Stall Model - Positive Stall AOA (deg): 6.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -6.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.65 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.65 +AOA (deg) CL CD Cm25 +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -1.10180000000000 0.405000000000000 0 +-22 -1.06440000000000 0.329000000000000 0 +-20 -1.05540000000000 0.282000000000000 0 +-19.750 -1.3432 0.07827 0.07364 -0.0368 +-19.500 -1.3520 0.07412 0.06942 -0.0380 +-19.250 -1.3588 0.07026 0.06549 -0.0390 +-19.000 -1.3630 0.06671 0.06187 -0.0399 +-18.750 -1.3640 0.06359 0.05867 -0.0407 +-18.500 -1.3727 0.05963 0.05465 -0.0415 +-18.250 -1.3785 0.05608 0.05105 -0.0422 +-18.000 -1.3809 0.05296 0.04787 -0.0427 +-17.750 -1.3805 0.05018 0.04503 -0.0430 +-17.500 -1.3775 0.04772 0.04250 -0.0433 +-17.250 -1.3782 0.04492 0.03965 -0.0435 +-17.000 -1.3782 0.04225 0.03694 -0.0436 +-16.750 -1.3750 0.03997 0.03462 -0.0436 +-16.500 -1.3687 0.03803 0.03263 -0.0435 +-16.250 -1.3613 0.03623 0.03077 -0.0433 +-16.000 -1.3583 0.03408 0.02860 -0.0429 +-15.750 -1.3521 0.03228 0.02677 -0.0425 +-15.500 -1.3428 0.03079 0.02525 -0.0420 +-15.250 -1.3326 0.02943 0.02384 -0.0415 +-15.000 -1.3257 0.02784 0.02225 -0.0407 +-14.750 -1.3161 0.02652 0.02091 -0.0399 +-14.500 -1.3036 0.02546 0.01981 -0.0392 +-14.250 -1.2929 0.02431 0.01864 -0.0383 +-14.000 -1.2826 0.02319 0.01751 -0.0372 +-13.750 -1.2700 0.02226 0.01657 -0.0361 +-13.500 -1.2556 0.02150 0.01577 -0.0351 +-13.250 -1.2456 0.02055 0.01483 -0.0335 +-13.000 -1.2336 0.01979 0.01407 -0.0319 +-12.750 -1.2204 0.01920 0.01346 -0.0303 +-12.500 -1.2131 0.01851 0.01277 -0.0277 +-12.250 -1.2076 0.01796 0.01222 -0.0245 +-12.000 -1.2041 0.01754 0.01179 -0.0208 +-11.750 -1.2064 0.01719 0.01142 -0.0159 +-11.500 -1.1882 0.01662 0.01088 -0.0150 +-11.250 -1.1585 0.01613 0.01039 -0.0162 +-11.000 -1.1294 0.01557 0.00986 -0.0173 +-10.750 -1.0982 0.01510 0.00941 -0.0186 +-10.500 -1.0669 0.01459 0.00894 -0.0201 +-10.250 -1.0385 0.01417 0.00853 -0.0207 +-10.000 -1.0087 0.01368 0.00809 -0.0217 +-9.750 -0.9774 0.01330 0.00772 -0.0228 +-9.500 -0.9478 0.01283 0.00731 -0.0237 +-9.250 -0.9247 0.01253 0.00701 -0.0229 +-9.000 -0.9015 0.01212 0.00664 -0.0222 +-8.750 -0.8817 0.01186 0.00638 -0.0207 +-8.500 -0.8619 0.01154 0.00607 -0.0192 +-8.250 -0.8432 0.01131 0.00585 -0.0174 +-8.000 -0.8229 0.01107 0.00561 -0.0159 +-7.750 -0.8009 0.01083 0.00538 -0.0147 +-7.500 -0.7780 0.01061 0.00516 -0.0137 +-7.250 -0.7551 0.01040 0.00495 -0.0128 +-7.000 -0.7311 0.01020 0.00476 -0.0120 +-6.750 -0.7074 0.01001 0.00456 -0.0111 +-6.500 -0.6827 0.00983 0.00438 -0.0105 +-6.250 -0.6583 0.00966 0.00420 -0.0098 +-6.000 -0.6331 0.00950 0.00405 -0.0092 +-5.750 -0.6081 0.00935 0.00389 -0.0086 +-5.500 -0.5827 0.00922 0.00375 -0.0080 +-5.250 -0.5571 0.00908 0.00361 -0.0075 +-5.000 -0.5317 0.00897 0.00348 -0.0070 +-4.750 -0.5056 0.00885 0.00336 -0.0065 +-4.500 -0.4799 0.00874 0.00324 -0.0061 +-4.250 -0.4538 0.00866 0.00314 -0.0056 +-4.000 -0.4278 0.00855 0.00304 -0.0052 +-3.750 -0.4013 0.00849 0.00296 -0.0048 +-3.500 -0.3754 0.00839 0.00286 -0.0044 +-3.250 -0.3483 0.00835 0.00280 -0.0041 +-3.000 -0.3226 0.00827 0.00272 -0.0036 +-2.500 -0.2691 0.00816 0.00260 -0.0029 +-2.250 -0.2421 0.00814 0.00255 -0.0027 +-2.000 -0.2155 0.00807 0.00250 -0.0023 +-1.750 -0.1886 0.00807 0.00246 -0.0020 +-1.500 -0.1618 0.00801 0.00242 -0.0017 +-1.250 -0.1347 0.00800 0.00240 -0.0015 +-1.000 -0.1080 0.00798 0.00237 -0.0011 +-0.750 -0.0808 0.00796 0.00235 -0.0009 +-0.250 -0.0269 0.00793 0.00233 -0.0003 +0.000 0.0000 0.00796 0.00233 0.0000 +0.250 0.0269 0.00793 0.00233 0.0003 +0.750 0.0808 0.00796 0.00235 0.0009 +1.000 0.1080 0.00798 0.00237 0.0011 +1.250 0.1347 0.00800 0.00240 0.0015 +1.500 0.1618 0.00801 0.00242 0.0017 +1.750 0.1886 0.00807 0.00246 0.0020 +2.000 0.2155 0.00807 0.00250 0.0023 +2.250 0.2421 0.00814 0.00255 0.0027 +2.500 0.2692 0.00816 0.00260 0.0029 +3.000 0.3227 0.00827 0.00272 0.0036 +3.250 0.3483 0.00835 0.00280 0.0041 +3.500 0.3754 0.00839 0.00286 0.0043 +3.750 0.4014 0.00849 0.00296 0.0048 +4.000 0.4279 0.00855 0.00304 0.0052 +4.250 0.4539 0.00866 0.00314 0.0056 +4.500 0.4800 0.00874 0.00324 0.0060 +4.750 0.5058 0.00885 0.00336 0.0065 +5.000 0.5318 0.00897 0.00348 0.0069 +5.250 0.5573 0.00908 0.00361 0.0075 +5.500 0.5829 0.00922 0.00375 0.0080 +5.750 0.6083 0.00935 0.00389 0.0085 +6.000 0.6333 0.00950 0.00405 0.0091 +6.250 0.6585 0.00966 0.00420 0.0097 +6.500 0.6829 0.00983 0.00438 0.0104 +6.750 0.7076 0.01001 0.00456 0.0111 +7.000 0.7314 0.01020 0.00476 0.0119 +7.250 0.7554 0.01040 0.00495 0.0127 +7.500 0.7784 0.01061 0.00516 0.0137 +7.750 0.8013 0.01083 0.00538 0.0146 +8.000 0.8233 0.01107 0.00561 0.0158 +8.250 0.8438 0.01131 0.00585 0.0172 +8.500 0.8625 0.01154 0.00607 0.0191 +8.750 0.8823 0.01186 0.00638 0.0206 +9.000 0.9021 0.01212 0.00664 0.0221 +9.250 0.9253 0.01252 0.00700 0.0228 +9.500 0.9483 0.01283 0.00730 0.0236 +9.750 0.9780 0.01329 0.00772 0.0227 +10.000 1.0093 0.01368 0.00808 0.0216 +10.250 1.0390 0.01416 0.00853 0.0206 +10.500 1.0676 0.01458 0.00893 0.0199 +10.750 1.0990 0.01510 0.00940 0.0185 +11.000 1.1302 0.01556 0.00985 0.0171 +11.250 1.1594 0.01612 0.01038 0.0160 +11.500 1.1891 0.01661 0.01086 0.0149 +11.750 1.2063 0.01717 0.01140 0.0159 +12.000 1.2043 0.01752 0.01177 0.0208 +12.250 1.2080 0.01794 0.01220 0.0245 +12.500 1.2137 0.01849 0.01275 0.0276 +12.750 1.2213 0.01918 0.01343 0.0302 +13.000 1.2347 0.01977 0.01405 0.0318 +13.250 1.2468 0.02053 0.01481 0.0333 +13.500 1.2570 0.02148 0.01575 0.0348 +13.750 1.2716 0.02223 0.01654 0.0358 +14.000 1.2842 0.02316 0.01748 0.0369 +14.250 1.2946 0.02428 0.01861 0.0380 +14.500 1.3057 0.02541 0.01976 0.0389 +14.750 1.3182 0.02648 0.02086 0.0396 +15.000 1.3279 0.02780 0.02220 0.0404 +15.250 1.3347 0.02939 0.02380 0.0412 +15.500 1.3454 0.03072 0.02518 0.0417 +15.750 1.3546 0.03222 0.02671 0.0421 +16.000 1.3609 0.03402 0.02854 0.0425 +16.250 1.3639 0.03617 0.03071 0.0429 +16.500 1.3719 0.03793 0.03253 0.0431 +16.750 1.3781 0.03987 0.03452 0.0432 +17.000 1.3814 0.04216 0.03685 0.0432 +17.250 1.3813 0.04484 0.03957 0.0431 +17.500 1.3813 0.04758 0.04236 0.0429 +17.750 1.3843 0.05004 0.04489 0.0426 +18.000 1.3848 0.05282 0.04773 0.0422 +18.250 1.3824 0.05595 0.05091 0.0417 +18.500 1.3766 0.05951 0.05452 0.0410 +18.750 1.3688 0.06336 0.05844 0.0402 +19.000 1.3675 0.06653 0.06168 0.0394 +19.250 1.3631 0.07010 0.06533 0.0385 +20 1.05540000000000 0.282000000000000 0 +22 1.06440000000000 0.329000000000000 0 +25 1.10180000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 + +Reynolds Number: 2e6 +BV Dyn. Stall Model - Positive Stall AOA (deg): 6.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -6.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.65 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.65 +AOA (deg) CL CD Cm25 +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -1.22300000000000 0.405000000000000 0 +-22 -1.18930000000000 0.329000000000000 0 +-20 -1.18120000000000 0.282000000000000 0 +-19 -1.17970000000000 0.145000000000000 0 +-18 -1.18140000000000 0.0285000000000000 0 +-17 -1.18240000000000 0.0260000000000000 0 +-16 -1.18230000000000 0.0236000000000000 0 +-15 -1.17470000000000 0.0215000000000000 0 +-14 -1.15800000000000 0.0196000000000000 0 +-13 -1.13050000000000 0.0179000000000000 0 +-12 -1.09060000000000 0.0162000000000000 0 +-11 -1.03980000000000 0.0148000000000000 0 +-10 -0.973900000000000 0.0135000000000000 0 +-9 -0.898600000000000 0.0124000000000000 0 +-8 -0.814300000000000 0.0114000000000000 0 +-7 -0.725400000000000 0.0105000000000000 0 +-6 -0.626800000000000 0.00980000000000000 0 +-5 -0.550000000000000 0.00920000000000000 0 +-4 -0.440000000000000 0.00890000000000000 0 +-3 -0.330000000000000 0.00860000000000000 0 +-2 -0.220000000000000 0.00840000000000000 0 +-1 -0.110000000000000 0.00830000000000000 0 +0 0 0.00820000000000000 0 +1 0.110000000000000 0.00830000000000000 0 +2 0.220000000000000 0.00840000000000000 0 +3 0.330000000000000 0.00860000000000000 0 +4 0.440000000000000 0.00890000000000000 0 +5 0.550000000000000 0.00920000000000000 0 +6 0.626800000000000 0.00980000000000000 0 +7 0.725400000000000 0.0105000000000000 0 +8 0.814300000000000 0.0114000000000000 0 +9 0.898600000000000 0.0124000000000000 0 +10 0.973900000000000 0.0135000000000000 0 +11 1.03980000000000 0.0148000000000000 0 +12 1.09060000000000 0.0162000000000000 0 +13 1.13050000000000 0.0179000000000000 0 +14 1.15800000000000 0.0196000000000000 0 +15 1.17470000000000 0.0215000000000000 0 +16 1.18230000000000 0.0236000000000000 0 +17 1.18240000000000 0.0260000000000000 0 +18 1.18140000000000 0.0285000000000000 0 +19 1.17970000000000 0.145000000000000 0 +20 1.18120000000000 0.282000000000000 0 +22 1.18930000000000 0.329000000000000 0 +25 1.22300000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 + +Reynolds Number: 5e6 +BV Dyn. Stall Model - Positive Stall AOA (deg): 6.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -6.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.76 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.76 +AOA (deg) CL CD Cm25 +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-25 -1.34760000000000 0.405000000000000 0 +-22 -1.31300000000000 0.329000000000000 0 +-20 -1.30540000000000 0.0293000000000000 0 +-19 -1.30660000000000 0.0268000000000000 0 +-18 -1.30310000000000 0.0245000000000000 0 +-17 -1.29770000000000 0.0224000000000000 0 +-16 -1.28600000000000 0.0205000000000000 0 +-15 -1.26800000000000 0.0186000000000000 0 +-14 -1.24100000000000 0.0170000000000000 0 +-13 -1.19790000000000 0.0156000000000000 0 +-12 -1.14530000000000 0.0143000000000000 0 +-11 -1.07870000000000 0.0132000000000000 0 +-10 -1.00490000000000 0.0121000000000000 0 +-9 -0.922200000000000 0.0112000000000000 0 +-8 -0.833400000000000 0.0104000000000000 0 +-7 -0.735400000000000 0.00970000000000000 0 +-6 -0.660000000000000 0.00910000000000000 0 +-5 -0.550000000000000 0.00860000000000000 0 +-4 -0.440000000000000 0.00830000000000000 0 +-3 -0.330000000000000 0.00810000000000000 0 +-2 -0.220000000000000 0.00790000000000000 0 +-1 -0.110000000000000 0.00780000000000000 0 +0 0 0.00780000000000000 0 +1 0.110000000000000 0.00780000000000000 0 +2 0.220000000000000 0.00790000000000000 0 +3 0.330000000000000 0.00810000000000000 0 +4 0.440000000000000 0.00830000000000000 0 +5 0.550000000000000 0.00860000000000000 0 +6 0.660000000000000 0.00910000000000000 0 +7 0.735400000000000 0.00970000000000000 0 +8 0.833400000000000 0.0104000000000000 0 +9 0.922200000000000 0.0112000000000000 0 +10 1.00490000000000 0.0121000000000000 0 +11 1.07870000000000 0.0132000000000000 0 +12 1.14530000000000 0.0143000000000000 0 +13 1.19790000000000 0.0156000000000000 0 +14 1.24100000000000 0.0170000000000000 0 +15 1.26800000000000 0.0186000000000000 0 +16 1.28600000000000 0.0205000000000000 0 +17 1.29770000000000 0.0224000000000000 0 +18 1.30310000000000 0.0245000000000000 0 +19 1.30660000000000 0.0268000000000000 0 +20 1.30540000000000 0.0293000000000000 0 +22 1.31300000000000 0.329000000000000 0 +25 1.34760000000000 0.405000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 + +Reynolds Number: 8e6 +BV Dyn. Stall Model - Positive Stall AOA (deg): 10.0 +BV Dyn. Stall Model - Negative Stall AOA (deg): -10.0 +LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.131 +LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.82 +LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.82 +AOA (deg) CL CD Cm25 +-180 0 0.0250000000000000 0 +-175 0.660000000000000 0.0550000000000000 0 +-170 0.850000000000000 0.140000000000000 0 +-165 0.680000000000000 0.230000000000000 0 +-160 0.635000000000000 0.320000000000000 0 +-155 0.670000000000000 0.420000000000000 0 +-150 0.770000000000000 0.575000000000000 0 +-145 0.900000000000000 0.755000000000000 0 +-140 0.980000000000000 0.925000000000000 0 +-135 0.930000000000000 1.08500000000000 0 +-130 0.850000000000000 1.22500000000000 0 +-125 0.760000000000000 1.35000000000000 0 +-120 0.670000000000000 1.46500000000000 0 +-115 0.575000000000000 1.55500000000000 0 +-110 0.450000000000000 1.63500000000000 0 +-105 0.320000000000000 1.70000000000000 0 +-100 0.185000000000000 1.75000000000000 0 +-95 0.0500000000000000 1.78000000000000 0 +-90 -0.0900000000000000 1.80000000000000 0 +-85 -0.230000000000000 1.80000000000000 0 +-80 -0.365000000000000 1.78000000000000 0 +-75 -0.500000000000000 1.73500000000000 0 +-70 -0.630000000000000 1.66500000000000 0 +-65 -0.760000000000000 1.57500000000000 0 +-60 -0.875000000000000 1.47000000000000 0 +-55 -0.955000000000000 1.34500000000000 0 +-50 -1.02000000000000 1.21500000000000 0 +-45 -1.05000000000000 1.07500000000000 0 +-40 -1.03500000000000 0.920000000000000 0 +-35 -0.980000000000000 0.745000000000000 0 +-30 -0.855000000000000 0.570000000000000 0 +-22 -1.45100000000000 0.329000000000000 0 +-20 -1.43500000000000 0.282000000000000 0 +-18 -1.41500000000000 0.135000000000000 0 +-16 -1.37700000000000 0.0199000000000000 0 +-15 -1.34400000000000 0.0184000000000000 0 +-14 -1.30100000000000 0.0170000000000000 0 +-13 -1.24800000000000 0.0157000000000000 0 +-12 -1.18200000000000 0.0145000000000000 0 +-11 -1.10800000000000 0.0134000000000000 0 +-10 -1.02400000000000 0.0124000000000000 0 +-9 -0.935000000000000 0.0115000000000000 0 +-8 -0.841000000000000 0.0107000000000000 0 +-7 -0.744000000000000 0.00990000000000000 0 +-6 -0.639000000000000 0.00930000000000000 0 +-5 -0.533000000000000 0.00880000000000000 0 +-4 -0.426000000000000 0.00840000000000000 0 +-3 -0.320000000000000 0.00800000000000000 0 +-2 -0.213000000000000 0.00780000000000000 0 +-1 -0.107000000000000 0.00770000000000000 0 +0 0 0.00760000000000000 0 +1 0.107000000000000 0.00770000000000000 0 +2 0.213000000000000 0.00780000000000000 0 +3 0.320000000000000 0.00800000000000000 0 +4 0.426000000000000 0.00840000000000000 0 +5 0.533000000000000 0.00880000000000000 0 +6 0.639000000000000 0.00930000000000000 0 +7 0.744000000000000 0.00990000000000000 0 +8 0.841000000000000 0.0107000000000000 0 +9 0.935000000000000 0.0115000000000000 0 +10 1.02400000000000 0.0124000000000000 0 +11 1.10800000000000 0.0134000000000000 0 +12 1.18200000000000 0.0145000000000000 0 +13 1.24800000000000 0.0157000000000000 0 +14 1.30100000000000 0.0170000000000000 0 +15 1.34400000000000 0.0184000000000000 0 +16 1.37700000000000 0.0199000000000000 0 +18 1.41500000000000 0.135000000000000 0 +20 1.43500000000000 0.282000000000000 0 +22 1.45100000000000 0.329000000000000 0 +30 0.855000000000000 0.570000000000000 0 +35 0.980000000000000 0.745000000000000 0 +40 1.03500000000000 0.920000000000000 0 +45 1.05000000000000 1.07500000000000 0 +50 1.02000000000000 1.21500000000000 0 +55 0.955000000000000 1.34500000000000 0 +60 0.875000000000000 1.47000000000000 0 +65 0.760000000000000 1.57500000000000 0 +70 0.630000000000000 1.66500000000000 0 +75 0.500000000000000 1.73500000000000 0 +80 0.365000000000000 1.78000000000000 0 +85 0.230000000000000 1.80000000000000 0 +90 0.0900000000000000 1.80000000000000 0 +95 -0.0500000000000000 1.78000000000000 0 +100 -0.185000000000000 1.75000000000000 0 +105 -0.320000000000000 1.70000000000000 0 +110 -0.450000000000000 1.63500000000000 0 +115 -0.575000000000000 1.55500000000000 0 +120 -0.670000000000000 1.46500000000000 0 +125 -0.760000000000000 1.35000000000000 0 +130 -0.850000000000000 1.22500000000000 0 +135 -0.930000000000000 1.08500000000000 0 +140 -0.980000000000000 0.925000000000000 0 +145 -0.900000000000000 0.755000000000000 0 +150 -0.770000000000000 0.575000000000000 0 +155 -0.670000000000000 0.420000000000000 0 +160 -0.635000000000000 0.320000000000000 0 +165 -0.680000000000000 0.230000000000000 0 +170 -0.850000000000000 0.140000000000000 0 +175 -0.660000000000000 0.0550000000000000 0 +180 0 0.0250000000000000 0 \ No newline at end of file diff --git a/examples/literate/data_RM2/3mx3m1pt2msNTM.inp b/examples/literate/data_RM2/3mx3m1pt2msNTM.inp new file mode 100644 index 00000000..919ebcad --- /dev/null +++ b/examples/literate/data_RM2/3mx3m1pt2msNTM.inp @@ -0,0 +1,70 @@ +---------TurbSim v2.00.* Input File------------------------ +Example input file for TurbSim. +---------Runtime Options----------------------------------- +False Echo - Echo input data to .ech (flag) +40071 RandSeed1 - First random seed (-2147483648 to 2147483647) +RANLUX RandSeed2 - Second random seed for intrinsic pRNG, or other pRNG: "RanLux" or "RNSNLW" +False WrBHHTP - Output HH turbulence parameters in GenPro-binary form? (Generates RootName.bin) +False WrFHHTP - Output HH turbulence parameters in formatted form? (Generates RootName.dat) +False WrADHH - Output hub-height time-series data in AeroDyn form? (Generates RootName.hh) +True WrADFF - Output FF time-series data in TurbSim/AeroDyn form? (Generates Rootname.bts) +False WrBLFF - Output FF time-series data in BLADED/AeroDyn form? (Generates RootName.wnd) +False WrADTWR - Output tower time-series data? (Generates RootName.twr) +False WrFMTFF - Output FF time-series data in formatted (readable) form? (RootName.u, .v, .w) +False WrACT - Output coherent turbulence time steps in AeroDyn form? (Generates RootName.cts) +True Clockwise - Clockwise rotation looking downwind? (Used only for FF binary files w/ BLADED) +0 ScaleIEC - Scale IEC turbulence models to exact target std deviation? [0=none;1=hub;2=all] + +--------Turbine/Model Specifications----------------------- +31 NumGrid_Z - Vertical grid-point matrix dimension +31 NumGrid_Y - Horizontal grid-point matrix dimension +0.1 TimeStep - Time step [s] +2 AnalysisTime- Length of analysis time series [s] (program will add time if necessary) +"ALL" UsableTime - Usable length of output time series [s] (GridWidth/MeanHHWS s added if not "ALL") +1.501 HubHt - Hub height [m] (should be > 0.5*GridHeight) +3.0 GridHeight - Grid height [m] +3.0 GridWidth - Grid width [m] (should be >= 2*(RotorRadius+ShaftLength)) +0 VFlowAng - Vertical mean flow (uptilt) angle [degrees] +0 HFlowAng - Horizontal mean flow (skew) angle [degrees] + +--------Meteorological Boundary Conditions------------------- +"IECKAI" TurbModel - Turbulence model (see Table 4 for valid codes) +"unused" UserFile - Name secondary input file for user-defined spectra or time series inputs +"1-ED3" IECstandard - Number of the IEC standard (61400-x, x=1,2,3) with optional 61400-1 ed. number +"A" IECturbc - IEC turbulence characteristic ("A", "B", "C" or TI in %) or KHTEST +"NTM" IEC_WindType- IEC turbulence type ("NTM", "xETM", "xEWM1", or "xEWM50" for x=class 1, 2, or 3) +default ETMc - IEC Extreme turbulence model "c" parameter [m/s] (or "default") +default ProfileType - Wind profile type (see Table 6 for valid codes) +"unused" ProfileFile - Name of the file that contains user-defined input profiles +1.501 RefHt - Height of the reference wind speed [m] +1.20 URef - Mean wind speed at the reference height [m/s] [must be 1-hr mean for API model] +450 ZJetMax - Height of the low-level jet [m] (70-490 m or "default", only for "JET" profile) +default PLExp - Power law exponent (or "default") +default Z0 - Surface roughness length [m] (or "default") + +--------Non-IEC Meteorological Boundary Conditions------------ +default Latitude - Site latitude [degrees] (or "default") +0.05 RICH_NO - Gradient Richardson number [-] +default UStar - Friction or shear velocity [m/s] (or "default") +default ZI - Mixing layer depth [m] (or "default") +default PC_UW - Hub mean u'w' Reynolds stress [m^2/s^2] (or "default" or "none") +default PC_UV - Hub mean u'v' Reynolds stress [m^2/s^2] (or "default" or "none") +default PC_VW - Hub mean v'w' Reynolds stress [m^2/s^2] (or "default" or "none") + +--------Spatial Coherence Parameters---------------------------- +default SCMod1 - u-component coherence model ("GENERAL","IEC","API","NONE", or "default") +default SCMod2 - v-component coherence model ("GENERAL","IEC","NONE", or "default") +default SCMod3 - w-component coherence model ("GENERAL","IEC","NONE", or "default") +default InCDec1 - u-component coherence parameters [-, m^-1] ("a b" in quotes or "default") +default InCDec2 - v-component coherence parameters [-, m^-1] ("a b" in quotes or "default") +default InCDec3 - w-component coherence parameters [-, m^-1] ("a b" in quotes or "default") +default CohExp - Coherence exponent for general model [-] (or "default") + +--------Coherent Turbulence Scaling Parameters------------------- +"path/to/coh_events/eventdata" CTEventPath - Name of the path where event data files are located +"Random" CTEventFile - Type of event files ("LES", "DNS", or "RANDOM") +True Randomize - Randomize the disturbance scale and locations? (true/false) +1.0 DistScl - Disturbance scale (ratio of wave height to rotor disk). +0.5 CTLy - Fractional location of tower center from right to L of dataset looking downwind +0.5 CTLz - Fractional location of hub height from the bottom of the dataset +30.0 CTStartTime - Minimum start time for coherent structures in RootName.cts [s] diff --git a/examples/literate/data_RM2/GeomBladesAD.csv b/examples/literate/data_RM2/GeomBladesAD.csv new file mode 100644 index 00000000..6ce90869 --- /dev/null +++ b/examples/literate/data_RM2/GeomBladesAD.csv @@ -0,0 +1,8 @@ +RM2,,,,# Shear webs ->,1,# of stacks ->,7,Stack ID ->,1,2,3,4,5,6,7,Segment ID ->,1,2,3,4,5,6,7,8,9,10,11,12,DP Types,1,2,3,4,5,6,7,8,9,10,11,12,1,2,3,4,5,6,7,8,9,10,11,12,, +,,,,,,# of segments ->,12,Material ID ->,1,1,1,1,1,1,1,,,,,,,,,,,,,,,,,,,,,,,,,,,first entry in the CSV list is the exterior blade surface stack,,,,,,,,,,,,SW1, +Sta.#,Blade span (m),Airfoil Shape File,TE Type,Twist (deg),Chord,xoffset,aero center,Section Label,LE,Panel_Face,Panel_Core,Spar,TE,SW_Face,SW_Core,-blank-,HP_TE,HP_Aft_Panel,HP_Aft_Spar,HP_Fore_Spar,HP_Fore_Panel,HP_LE,LP_LE,LP_Fore_Panel,LP_Aft_Spar,LP_Fore_Spar,LP_Aft_Panel,LP_TE,,,,,,,,,,,,,,HP_TE,HP_Aft_Panel,HP_Aft_Spar,HP_Fore_Spar,HP_Fore_Panel,HP_LE,LP_LE,LP_Fore_Panel,LP_Aft_Spar,LP_Fore_Spar,LP_Aft_Panel,LP_TE,stacks,dps +1,0,NACA_0021_AD,sharp,0,0.04,0.25,0.25,,0.000001,2.1,0.000001,0.000001,0.000001,0.000001,0.000001,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +2,0.20175,NACA_0021_AD,sharp,0,0.053335,0.25,0.25,,0.000001,2.8,0.000001,0.000001,0.000001,0.000001,0.000001,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +3,0.4035,NACA_0021_AD,sharp,0,0.06667,0.25,0.25,,0.000001,3.5,0.000001,0.000001,0.000001,0.000001,0.000001,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +4,0.60525,NACA_0021_AD,sharp,0,0.053335,0.25,0.25,,0.000001,2.8,0.000001,0.000001,0.000001,0.000001,0.000001,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +4,0.807,NACA_0021_AD,sharp,0,0.04,0.25,0.25,,0.000001,2.1,0.000001,0.000001,0.000001,0.000001,0.000001,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" diff --git a/examples/RM2/GeomBlades.csv b/examples/literate/data_RM2/GeomBladesDMS.csv similarity index 54% rename from examples/RM2/GeomBlades.csv rename to examples/literate/data_RM2/GeomBladesDMS.csv index 35ed9d21..4b251ce6 100644 --- a/examples/RM2/GeomBlades.csv +++ b/examples/literate/data_RM2/GeomBladesDMS.csv @@ -1,8 +1,8 @@ RM2,,,,# Shear webs ->,1,# of stacks ->,7,Stack ID ->,1,2,3,4,5,6,7,Segment ID ->,1,2,3,4,5,6,7,8,9,10,11,12,DP Types,1,2,3,4,5,6,7,8,9,10,11,12,1,2,3,4,5,6,7,8,9,10,11,12,, ,,,,,,# of segments ->,12,Material ID ->,1,1,1,1,1,1,1,,,,,,,,,,,,,,,,,,,,,,,,,,,first entry in the CSV list is the exterior blade surface stack,,,,,,,,,,,,SW1, Sta.#,Blade span (m),Airfoil Shape File,TE Type,Twist (deg),Chord,xoffset,aero center,Section Label,LE,Panel_Face,Panel_Core,Spar,TE,SW_Face,SW_Core,-blank-,HP_TE,HP_Aft_Panel,HP_Aft_Spar,HP_Fore_Spar,HP_Fore_Panel,HP_LE,LP_LE,LP_Fore_Panel,LP_Aft_Spar,LP_Fore_Spar,LP_Aft_Panel,LP_TE,,,,,,,,,,,,,,HP_TE,HP_Aft_Panel,HP_Aft_Spar,HP_Fore_Spar,HP_Fore_Panel,HP_LE,LP_LE,LP_Fore_Panel,LP_Aft_Spar,LP_Fore_Spar,LP_Aft_Panel,LP_TE,stacks,dps -1,0,NACA_0021,sharp,0,0.04,0.25,0.25,,0.000001,2.1,0.000001,0.000001,0.000001,0.000001,0.000001,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" -2,0.20175,NACA_0021,sharp,0,0.053335,0.25,0.25,,0.000001,2.8,0.000001,0.000001,0.000001,0.000001,0.000001,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" -3,0.4035,NACA_0021,sharp,0,0.06667,0.25,0.25,,0.000001,3.5,0.000001,0.000001,0.000001,0.000001,0.000001,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" -4,0.60525,NACA_0021,sharp,0,0.053335,0.25,0.25,,0.000001,2.8,0.000001,0.000001,0.000001,0.000001,0.000001,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" -4,0.807,NACA_0021,sharp,0,0.04,0.25,0.25,,0.000001,2.1,0.000001,0.000001,0.000001,0.000001,0.000001,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +1,0,NACA_0021_DMS,sharp,0,0.04,0.25,0.25,,0.000001,2.1,0.000001,0.000001,0.000001,0.000001,0.000001,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +2,0.20175,NACA_0021_DMS,sharp,0,0.053335,0.25,0.25,,0.000001,2.8,0.000001,0.000001,0.000001,0.000001,0.000001,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +3,0.4035,NACA_0021_DMS,sharp,0,0.06667,0.25,0.25,,0.000001,3.5,0.000001,0.000001,0.000001,0.000001,0.000001,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +4,0.60525,NACA_0021_DMS,sharp,0,0.053335,0.25,0.25,,0.000001,2.8,0.000001,0.000001,0.000001,0.000001,0.000001,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +4,0.807,NACA_0021_DMS,sharp,0,0.04,0.25,0.25,,0.000001,2.1,0.000001,0.000001,0.000001,0.000001,0.000001,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" diff --git a/examples/literate/data_RM2/GeomStrutsAD.csv b/examples/literate/data_RM2/GeomStrutsAD.csv new file mode 100644 index 00000000..f2e5b7b1 --- /dev/null +++ b/examples/literate/data_RM2/GeomStrutsAD.csv @@ -0,0 +1,9 @@ +RM2,,,,# Shear webs ->,1,# of stacks ->,7,Stack ID ->,1,2,3,4,5,6,7,Segment ID ->,1,2,3,4,5,6,7,8,9,10,11,12,DP Types,1,2,3,4,5,6,7,8,9,10,11,12,1,2,3,4,5,6,7,8,9,10,11,12,, +,,,,,,# of segments ->,12,Material ID ->,1,1,1,2,1,1,1,,,,,,,,,,,,,,,,,,,,,,,,,,,first entry in the CSV list is the exterior blade surface stack,,,,,,,,,,,,SW1, +Sta.#,Blade span (m),Airfoil Shape File,TE Type,Twist (deg),Chord,xoffset,aero center,Section Label,LE,Panel_Face,Panel_Core,Spar,TE,SW_Face,SW_Core,-blank-,HP_TE,HP_Aft_Panel,HP_Aft_Spar,HP_Fore_Spar,HP_Fore_Panel,HP_LE,LP_LE,LP_Fore_Panel,LP_Aft_Spar,LP_Fore_Spar,LP_Aft_Panel,LP_TE,,,,,,,,,,,,,,HP_TE,HP_Aft_Panel,HP_Aft_Spar,HP_Fore_Spar,HP_Fore_Panel,HP_LE,LP_LE,LP_Fore_Panel,LP_Aft_Spar,LP_Fore_Spar,LP_Aft_Panel,LP_TE,stacks,dps +1,0,NACA_0021_AD,sharp,0,0.06,0.25,0.25,,0.000001,3.15,0.000001,1,0.000001,0.000001,0.000001,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +2,0.079,NACA_0021_AD,sharp,0,0.06,0.25,0.25,,0.000001,3.15,0.000001,1,0.000001,0.000001,0.000001,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +3,0.08,NACA_0021_AD,sharp,0,0.06,0.25,0.25,,0.000001,3.15,0.000001,0.000001,0.000001,0.000001,0.000001,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +4,0.179,NACA_0021_AD,sharp,0,0.06,0.25,0.25,,0.000001,3.15,0.000001,0.000001,0.000001,0.000001,0.000001,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +5,0.3585,NACA_0021_AD,sharp,0,0.06,0.25,0.25,,0.000001,3.15,0.000001,0.000001,0.000001,0.000001,0.000001,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +6,0.5375,NACA_0021_AD,sharp,0,0.06,0.25,0.25,,0.000001,3.15,0.000001,0.000001,0.000001,0.000001,0.000001,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" \ No newline at end of file diff --git a/examples/literate/data_RM2/GeomStrutsDMS.csv b/examples/literate/data_RM2/GeomStrutsDMS.csv new file mode 100644 index 00000000..cb642d84 --- /dev/null +++ b/examples/literate/data_RM2/GeomStrutsDMS.csv @@ -0,0 +1,9 @@ +RM2,,,,# Shear webs ->,1,# of stacks ->,7,Stack ID ->,1,2,3,4,5,6,7,Segment ID ->,1,2,3,4,5,6,7,8,9,10,11,12,DP Types,1,2,3,4,5,6,7,8,9,10,11,12,1,2,3,4,5,6,7,8,9,10,11,12,, +,,,,,,# of segments ->,12,Material ID ->,1,1,1,2,1,1,1,,,,,,,,,,,,,,,,,,,,,,,,,,,first entry in the CSV list is the exterior blade surface stack,,,,,,,,,,,,SW1, +Sta.#,Blade span (m),Airfoil Shape File,TE Type,Twist (deg),Chord,xoffset,aero center,Section Label,LE,Panel_Face,Panel_Core,Spar,TE,SW_Face,SW_Core,-blank-,HP_TE,HP_Aft_Panel,HP_Aft_Spar,HP_Fore_Spar,HP_Fore_Panel,HP_LE,LP_LE,LP_Fore_Panel,LP_Aft_Spar,LP_Fore_Spar,LP_Aft_Panel,LP_TE,,,,,,,,,,,,,,HP_TE,HP_Aft_Panel,HP_Aft_Spar,HP_Fore_Spar,HP_Fore_Panel,HP_LE,LP_LE,LP_Fore_Panel,LP_Aft_Spar,LP_Fore_Spar,LP_Aft_Panel,LP_TE,stacks,dps +1,0,NACA_0021_DMS,sharp,0,0.06,0.25,0.25,,0.000001,3.15,0.000001,1,0.000001,0.000001,0.000001,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +2,0.079,NACA_0021_DMS,sharp,0,0.06,0.25,0.25,,0.000001,3.15,0.000001,1,0.000001,0.000001,0.000001,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +3,0.08,NACA_0021_DMS,sharp,0,0.06,0.25,0.25,,0.000001,3.15,0.000001,0.000001,0.000001,0.000001,0.000001,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +4,0.179,NACA_0021_DMS,sharp,0,0.06,0.25,0.25,,0.000001,3.15,0.000001,0.000001,0.000001,0.000001,0.000001,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +5,0.3585,NACA_0021_DMS,sharp,0,0.06,0.25,0.25,,0.000001,3.15,0.000001,0.000001,0.000001,0.000001,0.000001,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +6,0.5375,NACA_0021_DMS,sharp,0,0.06,0.25,0.25,,0.000001,3.15,0.000001,0.000001,0.000001,0.000001,0.000001,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" \ No newline at end of file diff --git a/examples/literate/data_RM2/RM2_0.538D_RE_D_0.9E6.csv b/examples/literate/data_RM2/RM2_0.538D_RE_D_0.9E6.csv new file mode 100644 index 00000000..50307852 --- /dev/null +++ b/examples/literate/data_RM2/RM2_0.538D_RE_D_0.9E6.csv @@ -0,0 +1,26 @@ +0.9913043478260869, -0.002177040975914979 +1.2521739130434777, -0.0013742049838391113 +1.5225296442687744, -0.0005726959934029829 +1.7739130434782604, 0.01366072359503695 +2.0252964426877464, 0.04971668514990368 +2.2719367588932804, 0.1269004085269333 +2.5233201581027664, 0.20324413986597267 +2.613438735177865, 0.23764400337437544 +2.7177865612648215, 0.2644879195457861 +2.8126482213438733, 0.28797584857015557 +2.9169960474308296, 0.3081051364442041 +3.021343873517786, 0.3282344243182528 +3.125691699604743, 0.3332557985232366 +3.225296442687746, 0.3307238793945079 +3.320158102766798, 0.32567463815508846 +3.424505928853754, 0.32398138406271015 +3.524110671936759, 0.31977080785964096 +3.6237154150197632, 0.3054882892105286 +3.7233201581027666, 0.2945630847100974 +3.8276679841897234, 0.28279788817167595 +3.9225296442687743, 0.27271267570923485 +4.017391304347826, 0.25759149202377213 +4.273517786561265, 0.21558923612098452 +4.520158102766798, 0.16603435038530434 +4.776284584980237, 0.11563880911081398 +5.0086956521739125, 0.06860389948910428 diff --git a/examples/literate/data_RM2/RM2_0.538D_RE_D_1.3E6.csv b/examples/literate/data_RM2/RM2_0.538D_RE_D_1.3E6.csv new file mode 100644 index 00000000..9700fe2e --- /dev/null +++ b/examples/literate/data_RM2/RM2_0.538D_RE_D_1.3E6.csv @@ -0,0 +1,16 @@ +1.000790513833992, 0.0062149173941478675 +1.2474308300395252, 0.006180415351513202 +1.5035573122529642, 0.027967128273665598 +1.7501976284584972, 0.053112482346138856 +1.9968379446640312, 0.1168669491284442 +2.2529644268774702, 0.1839774030577908 +2.4996047430830037, 0.2712330688808635 +2.60395256916996, 0.30479161334963634 +2.698814229249012, 0.3333155135970274 +2.803162055335968, 0.3551234585454165 +2.8980237154150195, 0.36350347390072113 +3.0023715415019763, 0.36516753395702395 +3.1067193675889326, 0.3651529369389862 +3.2015810276679835, 0.36681832399692876 +3.3059288537549403, 0.366803726978891 +3.400790513833992, 0.360075828665131 diff --git a/examples/RM2/TowerGeom.csv b/examples/literate/data_RM2/TowerGeom.csv similarity index 100% rename from examples/RM2/TowerGeom.csv rename to examples/literate/data_RM2/TowerGeom.csv diff --git a/examples/RM2/TowerMaterials.csv b/examples/literate/data_RM2/TowerMaterials.csv similarity index 100% rename from examples/RM2/TowerMaterials.csv rename to examples/literate/data_RM2/TowerMaterials.csv diff --git a/examples/RM2/Materials34m.csv b/examples/literate/data_RM2/materials_NuMAD.csv similarity index 100% rename from examples/RM2/Materials34m.csv rename to examples/literate/data_RM2/materials_NuMAD.csv diff --git a/src/SetupTurbine.jl b/src/SetupTurbine.jl index 2dd936e3..ee54ce0a 100644 --- a/src/SetupTurbine.jl +++ b/src/SetupTurbine.jl @@ -55,7 +55,8 @@ function setupOWENS(OWENSAero,path; meshtype = "Darrieus", custommesh = nothing, AddedMass_Coeff_Ca = 0.0, - verbosity=0) #Darrieus, H-VAWT, ARCUS + verbosity=0, + VTKmeshfilename = nothing) #Darrieus, H-VAWT, ARCUS custom_mesh_outputs = [] @@ -431,7 +432,7 @@ function setupOWENS(OWENSAero,path; #### store data in element object myel = OWENSFEA.El(sectionPropsArray,myort.Length,myort.Psi_d,myort.Theta_d,myort.Twist_d,rotationalEffects) - system, assembly, sections = OWENS.owens_to_gx(mymesh,myort,myjoint,sectionPropsArray,stiff_array,mass_array) + system, assembly, sections = OWENS.owens_to_gx(mymesh,myort,myjoint,sectionPropsArray,stiff_array,mass_array;VTKmeshfilename) nothing @@ -466,7 +467,15 @@ function setupOWENS(OWENSAero,path; end end - rhoA_in = [mass_bld[i][1,1] for i = 1:length(mass_bld)] + # Map the element wise mass to the input aero shape + rhoA_el = [mass_bld[i][1,1] for i = 1:length(mass_bld)] + if AD15bldNdIdxRng[1,2]