diff --git a/modules/aerodyn/ad_B1n2_OLAF/AD.dat b/modules/aerodyn/ad_B1n2_OLAF/AD.dat new file mode 100644 index 000000000..d764e2b47 --- /dev/null +++ b/modules/aerodyn/ad_B1n2_OLAF/AD.dat @@ -0,0 +1,92 @@ +------- AERODYN v15 for OpenFAST INPUT FILE ----------------------------------------------- +NREL 5.0 MW offshore baseline aerodynamic input properties. +====== General Options ============================================================================ +False Echo - Echo the input to ".AD.ech"? (flag) +"default" DTAero - Time interval for aerodynamic calculations {or "default"} (s) + 3 WakeMod - Type of wake/induction model (switch) {0=none, 1=BEMT, 2=DBEMT, 3=OLAF} [WakeMod cannot be 2 or 3 when linearizing] + 1 AFAeroMod - Type of blade airfoil aerodynamics model (switch) {1=steady model, 2=Beddoes-Leishman unsteady model} [AFAeroMod must be 1 when linearizing] + 0 TwrPotent - Type tower influence on wind based on potential flow around the tower (switch) {0=none, 1=baseline potential flow, 2=potential flow with Bak correction} + 0 TwrShadow - Calculate tower influence on wind based on downstream tower shadow (switch) {0=none, 1=Powles model, 2=Eames model} +False TwrAero - Calculate tower aerodynamic loads? (flag) +False FrozenWake - Assume frozen wake during linearization? (flag) [used only when WakeMod=1 and when linearizing] +False CavitCheck - Perform cavitation check? (flag) [AFAeroMod must be 1 when CavitCheck=true] +False Buoyancy - Include buoyancy effects? (flag) +False CompAA - Flag to compute AeroAcoustics calculation [used only when WakeMod = 1 or 2] +"unused" AA_InputFile - AeroAcoustics input file [used only when CompAA=true] +====== Environmental Conditions =================================================================== +"default" AirDens - Air density (kg/m^3) +"default" KinVisc - Kinematic viscosity of working fluid (m^2/s) +"default" SpdSound - Speed of sound in working fluid (m/s) +"default" Patm - Atmospheric pressure (Pa) [used only when CavitCheck=True] +"default" Pvap - Vapour pressure of working fluid (Pa) [used only when CavitCheck=True] +====== Blade-Element/Momentum Theory Options ====================================================== [unused when WakeMod=0 or 3] + 2 SkewMod - Type of skewed-wake correction model (switch) {1=uncoupled, 2=Pitt/Peters, 3=coupled} [unused when WakeMod=0 or 3] +"default" SkewModFactor - Constant used in Pitt/Peters skewed wake model {or "default" is 15/32*pi} (-) [used only when SkewMod=2; unused when WakeMod=0 or 3] +True TipLoss - Use the Prandtl tip-loss model? (flag) [unused when WakeMod=0 or 3] +True HubLoss - Use the Prandtl hub-loss model? (flag) [unused when WakeMod=0 or 3] +True TanInd - Include tangential induction in BEMT calculations? (flag) [unused when WakeMod=0 or 3] +False AIDrag - Include the drag term in the axial-induction calculation? (flag) [unused when WakeMod=0 or 3] +False TIDrag - Include the drag term in the tangential-induction calculation? (flag) [unused when WakeMod=0,3 or TanInd=FALSE] +"Default" IndToler - Convergence tolerance for BEMT nonlinear solve residual equation {or "default"} (-) [unused when WakeMod=0 or 3] + 100 MaxIter - Maximum number of iteration steps (-) [unused when WakeMod=0] +====== Dynamic Blade-Element/Momentum Theory Options ============================================== [used only when WakeMod=2] + 3 DBEMT_Mod - Type of dynamic BEMT (DBEMT) model {1=constant tau1, 2=time-dependent tau1, 3=constant tau1 with continuous formulation} (-) [used only when WakeMod=2] + 100 tau1_const - Time constant for DBEMT (s) [used only when WakeMod=2 and DBEMT_Mod=1 or 3] +====== OLAF -- cOnvecting LAgrangian Filaments (Free Vortex Wake) Theory Options ================== [used only when WakeMod=3] +"OLAF.dat" OLAFInputFileName - Input file for OLAF [used only when WakeMod=3] +====== Beddoes-Leishman Unsteady Airfoil Aerodynamics Options ===================================== [used only when AFAeroMod=2] + 4 UAMod - Unsteady Aero Model Switch (switch) {2=B-L Gonzalez, 3=B-L Minnema/Pierce, 4=B-L HGM 4-states, 5=B-L 5 states, 6=Oye, 7=Boeing-Vertol} [used only when AFAeroMod=2] +True FLookup - Flag to indicate whether a lookup for f' will be calculated (TRUE) or whether best-fit exponential equations will be used (FALSE); if FALSE S1-S4 must be provided in airfoil input files (flag) [used only when AFAeroMod=2] +====== Airfoil Information ========================================================================= + 3 AFTabMod - Interpolation method for multiple airfoil tables {1=1D interpolation on AoA (first table only); 2=2D interpolation on AoA and Re; 3=2D interpolation on AoA and UserProp} (-) + 1 InCol_Alfa - The column in the airfoil tables that contains the angle of attack (-) + 2 InCol_Cl - The column in the airfoil tables that contains the lift coefficient (-) + 3 InCol_Cd - The column in the airfoil tables that contains the drag coefficient (-) + 4 InCol_Cm - The column in the airfoil tables that contains the pitching-moment coefficient; use zero if there is no Cm column (-) + 0 InCol_Cpmin - The column in the airfoil tables that contains the Cpmin coefficient; use zero if there is no Cpmin column (-) + 1 NumAFfiles - Number of airfoil files used (-) +"NACA64_A17.dat" AFNames - Airfoil file names (NumAFfiles lines) (quoted strings) +====== Rotor/Blade Properties ===================================================================== +True UseBlCm - Include aerodynamic pitching moment in calculations? (flag) +"AD_blade.dat" ADBlFile(1) - Name of file containing distributed aerodynamic properties for Blade #1 (-) +"AD_blade.dat" ADBlFile(2) - Name of file containing distributed aerodynamic properties for Blade #2 (-) [unused if NumBl < 2] +"AD_blade.dat" ADBlFile(3) - Name of file containing distributed aerodynamic properties for Blade #3 (-) [unused if NumBl < 3] +====== Hub Properties ============================================================================== [used only when Buoyancy=True] +0.0 VolHub - Hub volume (m^3) +0.0 HubCenBx - Hub center of buoyancy x direction offset (m) +====== Nacelle Properties ========================================================================== [used only when Buoyancy=True] +0.0 VolNac - Nacelle volume (m^3) +0,0,0 NacCenB - Position of nacelle center of buoyancy from yaw bearing in nacelle coordinates (m) +====== Tail fin Aerodynamics ======================================================================== +False TFinAero - Calculate tail fin aerodynamics model (flag) +"unused" TFinFile - Input file for tail fin aerodynamics [used only when TFinAero=True] +====== Tower Influence and Aerodynamics ============================================================ [used only when TwrPotent/=0, TwrShadow/=0, TwrAero=True, or Buoyancy=True] + 2 NumTwrNds - Number of tower nodes used in the analysis (-) [used only when TwrPotent/=0, TwrShadow/=0, TwrAero=True, or Buoyancy=True] +TwrElev TwrDiam TwrCd TwrTI TwrCb !TwrTI used only with TwrShadow=2, TwrCb used only with Buoyancy=True +(m) (m) (-) (-) (-) +0.0000000E+00 6.0000000E+00 1.0000000E+00 1.0000000E-01 0.0 +90.000000E+00 3.8700000E+00 1.0000000E+00 1.0000000E-01 0.0 +====== Outputs ==================================================================================== +False SumPrint - Generate a summary file listing input options and interpolated properties to ".AD.sum"? (flag) + 0 NBlOuts - Number of blade node outputs [0 - 9] (-) + 0 BlOutNd - Blade nodes whose values will be output (-) + 0 NTwOuts - Number of tower node outputs [0 - 9] (-) + 0 TwOutNd - Tower nodes whose values will be output (-) + OutList - The next line(s) contains a list of output parameters. See OutListParameters.xlsx for a listing of available output channels, (-) +END of input file (the word "END" must appear in the first 3 columns of this last OutList line) +---------------------- NODE OUTPUTS -------------------------------------------- + 1 BldNd_BladesOut - Blades to output + 99 BldNd_BlOutNd - Blade nodes on each blade (currently unused) + OutList - The next line(s) contains a list of output parameters. See OutListParameters.xlsx, AeroDyn_Nodes tab for a listing of available output channels, (-) +"VUndx" - x-component of undisturbed wind velocity at each node +"VUndy" - y-component of undisturbed wind velocity at each node +"VUndz" - z-component of undisturbed wind velocity at each node +"STVx" - x-component of structural translational velocity at each node +"STVy" - y-component of structural translational velocity at each node +"STVz" - z-component of structural translational velocity at each node +"VRel" - Relvative wind speed at each node +"Vindx" - Axial induced wind velocity at each node +"Vindy" - Tangential induced wind velocity at each node +"Alpha" - Angle of attack at each node +"Fn" - Normal force (to chord) per unit length at each node +"Ft" - Tangential force (to chord) per unit length at each node diff --git a/modules/aerodyn/ad_B1n2_OLAF/AD_blade.dat b/modules/aerodyn/ad_B1n2_OLAF/AD_blade.dat new file mode 100644 index 000000000..3201d4c95 --- /dev/null +++ b/modules/aerodyn/ad_B1n2_OLAF/AD_blade.dat @@ -0,0 +1,8 @@ +------- AERODYN v15.00.* BLADE DEFINITION INPUT FILE ------------------------------------- +Based on NREL 5 MW but with less stations +====== Blade Properties ================================================================= + 2 NumBlNds - Number of blade nodes used in the analysis (-) + BlSpn BlCrvAC BlSwpAC BlCrvAng BlTwist BlChord BlAFID BlCb BlCenBn BlCenBt + (m) (m) (m) (deg) (deg) (m) (-) (-) (m) (m) +0.0000000E+00 0.0000000E+00 0.0000000E+00 0.0000000E+00 0.0000000E+00 2.0000000E+00 1 0.0 0.0 0.0 +20.000000E+00 0.0000000E+00 0.0000000E+00 0.0000000E+00 0.0000000E+00 2.0000000E+00 1 0.0 0.0 0.0 diff --git a/modules/aerodyn/ad_B1n2_OLAF/NACA64_A17.dat b/modules/aerodyn/ad_B1n2_OLAF/NACA64_A17.dat new file mode 100644 index 000000000..b5193fd98 --- /dev/null +++ b/modules/aerodyn/ad_B1n2_OLAF/NACA64_A17.dat @@ -0,0 +1,181 @@ +! ------------ AirfoilInfo v1.01.x Input File ---------------------------------- +! NACA64 airfoil with an aspect ratio of 17. Original -180 to 180deg Cl, Cd, and Cm versus AOA data taken from Appendix A of DOWEC document 10046_009.pdf (numerical values obtained from Koert Lindenburg of ECN). +! Cl and Cd values corrected for rotational stall delay and Cd values corrected using the Viterna method for 0 to 90deg AOA by Jason Jonkman using AirfoilPrep_v2p0.xls. +! note that this file uses Marshall Buhl's new input file processing; start all comment lines with ! +! ------------------------------------------------------------------------------ +"DEFAULT" InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=1] + 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) +@"NACA64_A17_coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +"unused" BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. + 1 NumTabs ! Number of airfoil tables in this file. +! ------------------------------------------------------------------------------ +! data for table 1 +! ------------------------------------------------------------------------------ + 0.75 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ + -4.432 alpha0 ! 0-lift angle of attack, depends on airfoil. + 9 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) + -9 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] + 0 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] + 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 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] + 1.4073 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. + -0.7945 Cn2 ! As Cn1 for negative AOAs. + 0.19 St_sh ! Strouhal's shedding frequency constant. [default = 0.19] + 0.0065 Cd0 ! 2D drag coefficient value at 0-lift. + -0.088 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 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] + 0 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 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 ! Reduced frequency cut-off for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (-) [default = 0.5] +!........................................ +! Table of aerodynamics coefficients + 127 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) + -180.00 0.000 0.0198 0.0000 + -175.00 0.374 0.0341 0.1880 + -170.00 0.749 0.0955 0.3770 + -160.00 0.659 0.2807 0.2747 + -155.00 0.736 0.3919 0.3130 + -150.00 0.783 0.5086 0.3428 + -145.00 0.803 0.6267 0.3654 + -140.00 0.798 0.7427 0.3820 + -135.00 0.771 0.8537 0.3935 + -130.00 0.724 0.9574 0.4007 + -125.00 0.660 1.0519 0.4042 + -120.00 0.581 1.1355 0.4047 + -115.00 0.491 1.2070 0.4025 + -110.00 0.390 1.2656 0.3981 + -105.00 0.282 1.3104 0.3918 + -100.00 0.169 1.3410 0.3838 + -95.00 0.052 1.3572 0.3743 + -90.00 -0.067 1.3587 0.3636 + -85.00 -0.184 1.3456 0.3517 + -80.00 -0.299 1.3181 0.3388 + -75.00 -0.409 1.2765 0.3248 + -70.00 -0.512 1.2212 0.3099 + -65.00 -0.606 1.1532 0.2940 + -60.00 -0.689 1.0731 0.2772 + -55.00 -0.759 0.9822 0.2595 + -50.00 -0.814 0.8820 0.2409 + -45.00 -0.850 0.7742 0.2212 + -40.00 -0.866 0.6610 0.2006 + -35.00 -0.860 0.5451 0.1789 + -30.00 -0.829 0.4295 0.1563 + -25.00 -0.853 0.3071 0.1156 + -24.00 -0.870 0.2814 0.1040 + -23.00 -0.890 0.2556 0.0916 + -22.00 -0.911 0.2297 0.0785 + -21.00 -0.934 0.2040 0.0649 + -20.00 -0.958 0.1785 0.0508 + -19.00 -0.982 0.1534 0.0364 + -18.00 -1.005 0.1288 0.0218 + -17.00 -1.082 0.1037 0.0129 + -16.00 -1.113 0.0786 -0.0028 + -15.00 -1.105 0.0535 -0.0251 + -14.00 -1.078 0.0283 -0.0419 + -13.50 -1.053 0.0158 -0.0521 + -13.00 -1.015 0.0151 -0.0610 + -12.00 -0.904 0.0134 -0.0707 + -11.00 -0.807 0.0121 -0.0722 + -10.00 -0.711 0.0111 -0.0734 + -9.00 -0.595 0.0099 -0.0772 + -8.00 -0.478 0.0091 -0.0807 + -7.00 -0.375 0.0086 -0.0825 + -6.00 -0.264 0.0082 -0.0832 + -5.00 -0.151 0.0079 -0.0841 + -4.00 -0.017 0.0072 -0.0869 + -3.00 0.088 0.0064 -0.0912 + -2.00 0.213 0.0054 -0.0946 + -1.00 0.328 0.0052 -0.0971 + 0.00 0.442 0.0052 -0.1014 + 1.00 0.556 0.0052 -0.1076 + 2.00 0.670 0.0053 -0.1126 + 3.00 0.784 0.0053 -0.1157 + 4.00 0.898 0.0054 -0.1199 + 5.00 1.011 0.0058 -0.1240 + 6.00 1.103 0.0091 -0.1234 + 7.00 1.181 0.0113 -0.1184 + 8.00 1.257 0.0124 -0.1163 + 8.50 1.293 0.0130 -0.1163 + 9.00 1.326 0.0136 -0.1160 + 9.50 1.356 0.0143 -0.1154 + 10.00 1.382 0.0150 -0.1149 + 10.50 1.400 0.0267 -0.1145 + 11.00 1.415 0.0383 -0.1143 + 11.50 1.425 0.0498 -0.1147 + 12.00 1.434 0.0613 -0.1158 + 12.50 1.443 0.0727 -0.1165 + 13.00 1.451 0.0841 -0.1153 + 13.50 1.453 0.0954 -0.1131 + 14.00 1.448 0.1065 -0.1112 + 14.50 1.444 0.1176 -0.1101 + 15.00 1.445 0.1287 -0.1103 + 15.50 1.447 0.1398 -0.1109 + 16.00 1.448 0.1509 -0.1114 + 16.50 1.444 0.1619 -0.1111 + 17.00 1.438 0.1728 -0.1097 + 17.50 1.439 0.1837 -0.1079 + 18.00 1.448 0.1947 -0.1080 + 18.50 1.452 0.2057 -0.1090 + 19.00 1.448 0.2165 -0.1086 + 19.50 1.438 0.2272 -0.1077 + 20.00 1.428 0.2379 -0.1099 + 21.00 1.401 0.2590 -0.1169 + 22.00 1.359 0.2799 -0.1190 + 23.00 1.300 0.3004 -0.1235 + 24.00 1.220 0.3204 -0.1393 + 25.00 1.168 0.3377 -0.1440 + 26.00 1.116 0.3554 -0.1486 + 28.00 1.015 0.3916 -0.1577 + 30.00 0.926 0.4294 -0.1668 + 32.00 0.855 0.4690 -0.1759 + 35.00 0.800 0.5324 -0.1897 + 40.00 0.804 0.6452 -0.2126 + 45.00 0.793 0.7573 -0.2344 + 50.00 0.763 0.8664 -0.2553 + 55.00 0.717 0.9708 -0.2751 + 60.00 0.656 1.0693 -0.2939 + 65.00 0.582 1.1606 -0.3117 + 70.00 0.495 1.2438 -0.3285 + 75.00 0.398 1.3178 -0.3444 + 80.00 0.291 1.3809 -0.3593 + 85.00 0.176 1.4304 -0.3731 + 90.00 0.053 1.4565 -0.3858 + 95.00 -0.074 1.4533 -0.3973 + 100.00 -0.199 1.4345 -0.4075 + 105.00 -0.321 1.4004 -0.4162 + 110.00 -0.436 1.3512 -0.4231 + 115.00 -0.543 1.2874 -0.4280 + 120.00 -0.640 1.2099 -0.4306 + 125.00 -0.723 1.1196 -0.4304 + 130.00 -0.790 1.0179 -0.4270 + 135.00 -0.840 0.9064 -0.4196 + 140.00 -0.868 0.7871 -0.4077 + 145.00 -0.872 0.6627 -0.3903 + 150.00 -0.850 0.5363 -0.3665 + 155.00 -0.798 0.4116 -0.3349 + 160.00 -0.714 0.2931 -0.2942 + 170.00 -0.749 0.0971 -0.3771 + 175.00 -0.374 0.0334 -0.1879 + 180.00 0.000 0.0198 0.0000 diff --git a/modules/aerodyn/ad_B1n2_OLAF/NACA64_A17_coords.txt b/modules/aerodyn/ad_B1n2_OLAF/NACA64_A17_coords.txt new file mode 100644 index 000000000..aa31ac26b --- /dev/null +++ b/modules/aerodyn/ad_B1n2_OLAF/NACA64_A17_coords.txt @@ -0,0 +1,407 @@ + 400 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 +0.25 0 +! coordinates of airfoil shape; data from TU Delft as posted here: https://wind.nrel.gov/forum/wind/viewtopic.php?f=2&t=440 +! NACA 64-618 (interpolated to 399 points) +! x/c y/c +1.000000 0.000000 +0.990000 0.003385 +0.980000 0.006126 +0.975000 0.007447 +0.970000 0.008767 +0.965000 0.010062 +0.960000 0.011357 +0.955000 0.012639 +0.950000 0.013921 +0.945000 0.015200 +0.940000 0.016478 +0.935000 0.017757 +0.930000 0.019036 +0.925000 0.020317 +0.920000 0.021598 +0.915000 0.022881 +0.910000 0.024163 +0.905000 0.025448 +0.900000 0.026733 +0.887500 0.029951 +0.875000 0.033169 +0.862500 0.036386 +0.850000 0.039603 +0.837500 0.042804 +0.825000 0.046004 +0.812500 0.049171 +0.800000 0.052337 +0.787500 0.055452 +0.775000 0.058566 +0.762500 0.061611 +0.750000 0.064656 +0.737500 0.067615 +0.725000 0.070573 +0.712500 0.073429 +0.700000 0.076285 +0.687500 0.079029 +0.675000 0.081773 +0.662500 0.084393 +0.650000 0.087012 +0.637500 0.089490 +0.625000 0.091967 +0.612500 0.094283 +0.600000 0.096599 +0.587500 0.098743 +0.575000 0.100887 +0.562500 0.102843 +0.550000 0.104799 +0.537500 0.106549 +0.525000 0.108299 +0.512500 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b/modules/aerodyn/ad_B1n2_OLAF/OLAF.dat @@ -0,0 +1,48 @@ +--------------------------- FREE WAKE INPUT FILE ---------------------------------------------- +Free wake input file for the BAR turbine +--------------------------- GENERAL OPTIONS --------------------------------------------------- +default IntMethod - Integration method {1: RK4, 5: Forward Euler 1st order, default: 5} (switch) +default DTfvw - Time interval for wake propagation. {default: dtaero} (s) +default FreeWakeStart - Time when wake is free. (-) value = always free. {default: 0.0} (s) +0.0 FullCircStart - Time at which full circulation is reached. {default: 0.0} (s) +-------------------------- CIRCULATION SPECIFICATIONS ---------------------------------------- +default CircSolvMethod - Circulation solving method {1: Cl-Based, 2: No-Flow Through, 3: Prescribed, default: 1 }(switch) +default CircSolvConvCrit - Convergence criteria {default: 0.001} [only if CircSolvMethod=1] (-) +default CircSolvRelaxation - Relaxation factor {default: 0.1} [only if CircSolvMethod=1] (-) +default CircSolvMaxIter - Maximum number of iterations for circulation solving {default: 30} (-) +"NA" PrescribedCircFile - File containing prescribed circulation [only if CircSolvMethod=3] (quoted string) +=============================================================================================== +--------------------------- WAKE OPTIONS ------------------------------------------------------ +------------------- WAKE EXTENT AND DISCRETIZATION -------------------------------------------- +100 nNWPanels - Number of near-wake panels (-) +default nNWPanelsFree - Number of free near-wake panels (-) {default: nNWPanels} +0 nFWPanels - Number of far-wake panels (-) {default: 0} +0 nFWPanelsFree - Number of free far-wake panels (-) {default: nFWPanels} +default FWShedVorticity - Include shed vorticity in the far wake {default: False} +------------------- WAKE REGULARIZATIONS AND DIFFUSION ----------------------------------------- +default DiffusionMethod - Diffusion method to account for viscous effects {0: None, 1: Core Spreading, "default": 0} +0 RegDeterMethod - Method to determine the regularization parameters {0: Manual, 1: Optimized, 2: Chord, 3: Span, default: 0 } +default RegFunction - Viscous diffusion function {0: None, 1: Rankine, 2: LambOseen, 3: Vatistas, 4: Denominator, "default": 3} (switch) +default WakeRegMethod - Wake regularization method {1: Constant, 2: Stretching, 3: Age, default: 3} (switch) +1.5 WakeRegFactor - Wake regularization factor (m or -) +1.5 WingRegFactor - Wing regularization factor (m or -) +1000 CoreSpreadEddyVisc - Eddy viscosity in core spreading methods, typical values 1-1000 +------------------- WAKE TREATMENT OPTIONS --------------------------------------------------- +False TwrShadowOnWake - Include tower flow disturbance effects on wake convection {default:false} [only if TwrPotent or TwrShadow] +default ShearModel - Shear Model {0: No treatment, 1: Mirrored vorticity, default: 0} +------------------- SPEEDUP OPTIONS ----------------------------------------------------------- +2 VelocityMethod - Method to determine the velocity {1:Segment N^2, 2:Particle tree, 3:Particle N^2, 4:Segment tree, default: 2} +default TreeBranchFactor - Branch radius fraction above which a multipole calculation is used {default: 1.5} [only if VelocityMethod=2,4] +default PartPerSegment - Number of particles per segment {default: 1} [only if VelocityMethod=2,3] +=============================================================================================== +--------------------------- OUTPUT OPTIONS --------------------------------------------------- +1 WrVTk - Outputs Visualization Toolkit (VTK) (independent of .fst option) {0: NoVTK, 1: Write VTK at VTK_fps, 2: Write VTK at init and final, default: 0} (flag) +0 nVTKBlades - Number of blades for which VTK files are exported {0: No VTK per blade, n: VTK for blade 1 to n, default: 0} (-) +1 VTKCoord - Coordinate system used for VTK export. {1: Global, 2: Hub, 3: Both, default: 1} +all VTK_fps - Frame rate for VTK output (frames per second) {"all" for all glue code timesteps, "default" for all OLAF timesteps} [only if WrVTK=1] +0 nGridOut - Number of grid outputs +GridName GridType TStart TEnd DTGrid XStart XEnd nX YStart YEnd nY ZStart ZEnd nZ +(-) (-) (s) (s) (s) (m) (m) (-) (m) (m) (-) (m) (m) (-) +=============================================================================================== +--------------------------- ADVANCED OPTIONS -------------------------------------------------- +=============================================================================================== diff --git a/modules/aerodyn/ad_B1n2_OLAF/README.md b/modules/aerodyn/ad_B1n2_OLAF/README.md new file mode 100644 index 000000000..44227f594 --- /dev/null +++ b/modules/aerodyn/ad_B1n2_OLAF/README.md @@ -0,0 +1,2 @@ +# One Rotating Blade with two aerodynamic section + diff --git a/modules/aerodyn/ad_B1n2_OLAF/ad_driver.dvr b/modules/aerodyn/ad_B1n2_OLAF/ad_driver.dvr new file mode 100644 index 000000000..861850545 --- /dev/null +++ b/modules/aerodyn/ad_B1n2_OLAF/ad_driver.dvr @@ -0,0 +1,56 @@ +----- AeroDyn Driver Input File --------------------------------------------------------- +BAR turbine driver input file, using basic input +----- Input Configuration --------------------------------------------------------------- +False Echo - Echo input parameters to ".ech"? + 0 MHK - MHK turbine type (switch) {0: not an MHK turbine, 1: fixed MHK turbine, 2: floating MHK turbine} + 1 AnalysisType - {1: multiple turbines, one simulation, 2: one turbine, one time-dependent simulation, 3: one turbine, combined cases} + 6.0 TMax - Total run time [used only when AnalysisType/=3] (s) + 0.1 DT - Simulation time step [used only when AnalysisType/=3] (s) +"AD.dat" AeroFile - Name of the primary AeroDyn input file +----- Environmental Conditions ---------------------------------------------------------- + 1.225000000000000e+00 FldDens - Density of working fluid (kg/m^3) + 1.477551020408163e-05 KinVisc - Kinematic viscosity of working fluid (m^2/s) + 3.350000000000000e+02 SpdSound - Speed of sound in working fluid (m/s) + 1.035000000000000e+05 Patm - Atmospheric pressure (Pa) [used only for an MHK turbine cavitation check] + 1.700000000000000e+03 Pvap - Vapour pressure of working fluid (Pa) [used only for an MHK turbine cavitation check] + 0 WtrDpth - Water depth (m) +----- Inflow Data --------------------------------------------------------------- + 0 CompInflow - Compute inflow wind velocities (switch) {0=Steady Wind; 1=InflowWind} +"unused" InflowFile - Name of the InflowWind input file [used only when CompInflow=1] + 2.0 HWindSpeed - Horizontal wind speed [used only when CompInflow=0 and AnalysisType=1] (m/s) + 90 RefHt - Reference height for horizontal wind speed [used only when CompInflow=0] (m) + 0.80 PLExp - Power law exponent [used only when CompInflow=0 and AnalysisType=1] (-) +----- Turbine Data ---------------------------------------------------------------------- +1 NumTurbines - Number of turbines +----- Turbine(1) ------------------------------------------------------------------------ + True BasicHAWTFormat(1) - Flag to switch between basic or generic input format {True: next 7 lines are basic inputs, False: Base/Twr/Nac/Hub/Bld geometry and motion must follow} + 0,0,0 BaseOriginInit(1) - Coordinate of tower base in base coordinates (m) + 1 NumBlades(1) - Number of blades (-) + 10. HubRad(1) - Hub radius (m) + 90.0 HubHt(1) - Hub height (m) + -10 Overhang(1) - Overhang (m) + -5 ShftTilt(1) - Shaft tilt (deg) + 0 Precone(1) - Blade precone (deg) + 0.0 Twr2Shft(1) - Vertical distance from the tower-top to the rotor shaft (m) +----- Turbine(1) Motion [used only when AnalysisType=1] --------------------------------- +0 BaseMotionType(1) - Type of motion prescribed for this base {0: fixed, 1: Sinusoidal motion, 2: arbitrary motion} (flag) +0 DegreeOfFreedom(1) - {1:xt, 2:yt, 3:zt, 4:theta_xt, 5:theta_yt, 6:theta_zt} [used only when BaseMotionType=1] (flag) +0 Amplitude(1) - Amplitude of sinusoidal motion [used only when BaseMotionType=1] (m or rad) +0 Frequency(1) - Frequency of sinusoidal motion [used only when BaseMotionType=1] (Hz) +"" BaseMotionFileName(1) - Filename containing arbitrary base motion (19 columns: Time, x, y, z, theta_x, ..., alpha_z) [used only when BaseMotionType=2] +0 NacYaw(1) - Yaw angle (about z_t) of the nacelle (deg) +10 RotSpeed(1) - Rotational speed of rotor in rotor coordinates (rpm) +0 BldPitch(1) - Blade 1 pitch (deg) +----- Time-dependent Analysis [used only when AnalysisType=2, numTurbines=1] ------------ +"unused" TimeAnalysisFileName - Filename containing time series (6 column: Time, HWndSpeed, PLExp, RotSpd, Pitch, Yaw). +----- Combined-Case Analysis [used only when AnalysisType=3, numTurbines=1] ------------- + 0 NumCases - Number of cases to run +HWndSpeed PLExp RotSpd Pitch Yaw dT Tmax DOF Amplitude Frequency +(m/s) (-) (rpm) (deg) (deg) (s) (s) (-) (m or rad) (Hz) +----- Output Settings ------------------------------------------------------------------- +"ES15.8E2" OutFmt - Format used for text tabular output, excluding the time channel. Resulting field should be 10 characters. (quoted string) +2 OutFileFmt - Format for tabular (time-marching) output file (switch) {1: text file [.out], 2: binary file [.outb], 3: both} +0 WrVTK - VTK visualization data output: (switch) {0=none; 1=init; 2=animation} +1 WrVTK_Type - VTK visualization data type: (switch) {1=surfaces; 2=lines; 3=both} +2 VTKHubRad - HubRadius for VTK visualization (m) +-1,-1,-1,2,2,2 VTKNacDim - Nacelle Dimension for VTK visualization x0,y0,z0,Lx,Ly,Lz (m) diff --git a/modules/aerodyn/ad_B1n2_OLAF/ad_driver.outb b/modules/aerodyn/ad_B1n2_OLAF/ad_driver.outb new file mode 100644 index 000000000..0107a9d30 Binary files /dev/null and b/modules/aerodyn/ad_B1n2_OLAF/ad_driver.outb differ diff --git a/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/py_ad_driver.py b/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/py_ad_driver.py index caa8d0941..3eae013e4 100644 --- a/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/py_ad_driver.py +++ b/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/py_ad_driver.py @@ -28,18 +28,16 @@ # set necessary library values # set input file string arrays (from file or script) # 2. initialize AeroDyn Fortran library -# set initial position, velocity, acceleration values -# call aerodyn_inflow_init once to initialize IfW -# Handle any resulting errors +# - ADI_PreInit -- set number of turbines +# - ADI_SetupTurb -- initialize one rotor (iterate over turbines) +# - ADI_Init -- actually call ADI to initialize the simulation # 3. timestep iteration -# set extrapolated values for inputs -# call aerodyn_inflow_updatestates to propogate forwared from t to t+dt -# set position, velocity, and accleration information for all nodes -# call aerodyn_inflow_calcoutput. Handle any resulting errors -# return the resulting force and moment array -# aggregate output channnels +# - ADI_SetMotion -- set motions of single turbine (iterate over turbines) +# - ADI_UpdateStates -- update to next timestep +# - ADI_CalcOutput -- get outputs +# - ADI_GetRotorLoads -- get loads per rotor (iterate over turbines) # 4. End -# call aerodyn_inflow_end to close the AeroDyn library and free memory +# call adi_end to close the AeroDyn library and free memory # handle any resulting errors # # @@ -149,6 +147,10 @@ fh.close() +#=============================================================================== +# Number of turbines +numTurbines = 1 + #=============================================================================== # Initial hub and root locations from vtk files # can add checks here that numpts==1 @@ -250,6 +252,7 @@ def SetMotionBlMesh(N_Step): adilib.defPvap = 1700.0 # Vapour pressure of working fluid (Pa) [used only for an MHK turbine cavitation check] adilib.WtrDpth = 0.0 # Water depth (m) adilib.MSL2SWL = 0.0 # Offset between still-water level and mean sea level (m) [positive upward] +adilib.numTurbines = numTurbines # Setup some timekeeping -- this may be smaller than what is passed to AD15 adilib.numTimeSteps = TimeStepsToRun # only for constructing array of output channels for duration of simulation @@ -259,7 +262,7 @@ def SetMotionBlMesh(N_Step): adilib.storeHHvel = False adilib.WrVTK = 2 # animation adilib.WrVTK_Type = 3 # surface and line meshes -adilib.transposeDCM = True +adilib.transposeDCM = 1 # 0=false, 1=true #============================================================================== # Basic alogrithm for using AeroDyn+InflowWind library @@ -271,11 +274,7 @@ def SetMotionBlMesh(N_Step): # end up with memory leaks and a bunch of garbage in the other library # instances). -# Aero calculation method -- AeroProjMod -# APM_BEM_NoSweepPitchTwist - 1 - "Original AeroDyn model where momentum balance is done in the WithoutSweepPitchTwist system" -# APM_BEM_Polar - 2 - "Use staggered polar grid for momentum balance in each annulus" -# APM_LiftingLine - 3 - "Use the blade lifting line (i.e. the structural) orientation (currently for OLAF with VAWT)" -adilib.AeroProjMod = 1 +isHAWT = 1 # 1: HAWT, 0: VAWT or cross-flow # Set hub and blade root positions/orientations adilib.initHubPos = initHubPos[0,:] @@ -295,13 +294,34 @@ def SetMotionBlMesh(N_Step): adilib.initMeshPos = initMeshPos_ar adilib.initMeshOrient = initMeshOrient_ar -# AeroDyn_Inflow_Init: Only need to call aerodyn_inflow_init once +# ADI_PreInit: call before anything else +try: + adilib.adi_preinit() +except Exception as e: + print("{}".format(e)) # Exceptions handled in adi_library.py + #FIXME: temporary statement here + print("Exit after failed call to adi_preinit") + exit(1) + +# ADI_SetupRotor +try: + #FIXME: hard code to one turbine for now + iturb=1 + turbRefPos=[0,0,0] + adilib.adi_setuprotor(iturb,isHAWT,turbRefPos) +except Exception as e: + print("{}".format(e)) # Exceptions handled in adi_library.py + #FIXME: temporary statement here + print("Exit after failed call to adi_setuprotor") + exit(1) + +# ADI_Init: Only need to call adi_init once try: - adilib.aerodyn_inflow_init(adiAD_input_string_array,adiIfW_input_string_array) + adilib.adi_init(adiAD_input_string_array,adiIfW_input_string_array) except Exception as e: - print("{}".format(e)) # Exceptions handled in aerodyn_inflow_library.py + print("{}".format(e)) # Exceptions handled in adi_library.py #FIXME: temporary statement here - print("Exit after failed call to aerodyn_inflow_init") + print("Exit after failed call to adi_init") exit(1) @@ -334,22 +354,48 @@ def SetMotionBlMesh(N_Step): RootPos, RootOrient, RootVel, RootAcc = SetMotionRoot(i) MeshPos_ar, MeshOrient_ar, MeshVel_ar, MeshAcc_ar, MeshFrcMom = SetMotionBlMesh(i) -print(f"Time step: {i} at {time[i]}") +# Set initial motions for rotor 1 try: - adilib.aerodyn_inflow_calcOutput(time[i], + adilib.adi_setrotormotion( + iturb, HubPos, HubOrient, HubVel, HubAcc, NacPos, NacOrient, NacVel, NacAcc, RootPos, RootOrient, RootVel, RootAcc, - MeshPos_ar, MeshOrient_ar, MeshVel_ar, MeshAcc_ar, - MeshFrcMom, + MeshPos_ar, MeshOrient_ar, MeshVel_ar, MeshAcc_ar) +except Exception as e: + print("{}".format(e)) + if DbgOuts == 1: + dbg_outfile.end() + #FIXME: temporary statement here + print("Exit after failed call to adi_calcOutput at T=0") + exit(1) + + +print(f"Time step: {i} at {time[i]}") +try: + adilib.adi_calcOutput(time[i], outputChannelValues) except Exception as e: print("{}".format(e)) if DbgOuts == 1: dbg_outfile.end() #FIXME: temporary statement here - print("Exit after failed call to aerodyn_inflow_calcOutput at T=0") + print("Exit after failed call to adi_calcOutput at T=0") + exit(1) + +# get resulting forces +try: + adilib.adi_getrotorloads( + iturb, + MeshFrcMom) +except Exception as e: + print("{}".format(e)) + if DbgOuts == 1: + dbg_outfile.end() + #FIXME: temporary statement here + print("Exit after failed call to adi_getrotorloads at T=0") exit(1) + ## Write the debug output at t=t_initial if DbgOuts == 1: @@ -376,6 +422,9 @@ def SetMotionBlMesh(N_Step): # time[i] is at t+dt for i in range( 1, len(time)): + # hard code to one turbine for now + iturb = 1 + for correction in range(0, NumCorrections+1): #print(f"Correction step: {correction} for {time[i-1]} --> {time[i]}") @@ -388,20 +437,32 @@ def SetMotionBlMesh(N_Step): RootPos, RootOrient, RootVel, RootAcc = SetMotionRoot(i) MeshPos_ar, MeshOrient_ar, MeshVel_ar, MeshAcc_ar, MeshFrcMom = SetMotionBlMesh(i) + # Set motions for rotor + try: + adilib.adi_setrotormotion( + iturb, + HubPos, HubOrient, HubVel, HubAcc, + NacPos, NacOrient, NacVel, NacAcc, + RootPos, RootOrient, RootVel, RootAcc, + MeshPos_ar, MeshOrient_ar, MeshVel_ar, MeshAcc_ar) + except Exception as e: + print("{}".format(e)) + if DbgOuts == 1: + dbg_outfile.end() + #FIXME: temporary statement here + print("Exit after failed call to adi_setrotormotion at {time[i]}") + exit(1) + # Update the states from t to t+dt (only if not beyond end of sim) try: - adilib.aerodyn_inflow_updateStates(time[i-1], time[i], - HubPos, HubOrient, HubVel, HubAcc, - NacPos, NacOrient, NacVel, NacAcc, - RootPos, RootOrient, RootVel, RootAcc, - MeshPos_ar, MeshOrient_ar, MeshVel_ar, MeshAcc_ar) + adilib.adi_updateStates(time[i-1], time[i]) except Exception as e: print("{}".format(e)) if DbgOuts == 1: dbg_outfile.end() #FIXME: temporary statement here - print("Exit after failed call to aerodyn_inflow_updateStates") + print("Exit after failed call to adi_updateStates") exit(1) # Calculate the outputs at t+dt @@ -414,23 +475,49 @@ def SetMotionBlMesh(N_Step): RootPos, RootOrient, RootVel, RootAcc = SetMotionRoot(i) MeshPos_ar, MeshOrient_ar, MeshVel_ar, MeshAcc_ar, MeshFrcMom = SetMotionBlMesh(i) + # Set motions for rotor + try: + adilib.adi_setrotormotion( + iturb, + HubPos, HubOrient, HubVel, HubAcc, + NacPos, NacOrient, NacVel, NacAcc, + RootPos, RootOrient, RootVel, RootAcc, + MeshPos_ar, MeshOrient_ar, MeshVel_ar, MeshAcc_ar) + except Exception as e: + print("{}".format(e)) + if DbgOuts == 1: + dbg_outfile.end() + #FIXME: temporary statement here + print("Exit after failed call to adi_setrotormotion at {time[i]}") + exit(1) + + try: - adilib.aerodyn_inflow_calcOutput(time[i], - HubPos, HubOrient, HubVel, HubAcc, - NacPos, NacOrient, NacVel, NacAcc, - RootPos, RootOrient, RootVel, RootAcc, - MeshPos_ar, MeshOrient_ar, MeshVel_ar, MeshAcc_ar, - MeshFrcMom, - outputChannelValues) + adilib.adi_calcOutput(time[i], outputChannelValues) except Exception as e: print("{}".format(e)) if DbgOuts == 1: dbg_outfile.end() #FIXME: temporary statement here - print(f"Exit after failed call to aerodyn_inflow_calcOutput at time {time[i]}") + print(f"Exit after failed call to adi_calcOutput at time {time[i]}") + exit(1) + + # get resulting forces + try: + adilib.adi_getrotorloads( + iturb, + MeshFrcMom) + except Exception as e: + print("{}".format(e)) + if DbgOuts == 1: + dbg_outfile.end() + #FIXME: temporary statement here + print("Exit after failed call to adi_getrotorloads at {time[i]}") exit(1) +## Write the debug output at t=t_initial + # When coupled to a different code, this is where the Force/Moment info # would be passed to the aerodynamic solver. # @@ -454,22 +541,25 @@ def SetMotionBlMesh(N_Step): if DbgOuts == 1: dbg_outfile.end() # close the debug output file +# if we got this far, things must have succeeded +print("Simulation completed sucessfully") + -# aerodyn_inflow_end: Only need to call aerodyn_inflow_end once. +# adi_end: Only need to call aerodyn_inflow_end once. # NOTE: in the event of an error during the above Init or CalcOutput calls, # the IfW_End routine will be called during that error handling. # This works for IfW, but may not be a desirable way to handle # errors in other codes (we may still want to retrieve some info # from memory before clearing out everything). -# NOTE: Error handling from the aerodyn_inflow_end call may not be entirely +# NOTE: Error handling from the adi_end call may not be entirely # necessary, but we may want to know if some memory was not released # properly or a file not closed correctly. try: - adilib.aerodyn_inflow_end() + adilib.adi_end() except Exception as e: print("{}".format(e)) #FIXME: temporary statement here - print("Exit after failed call to aerodyn_inflow_end") + print("Exit after failed call to adi_end") exit(1) diff --git a/modules/aerodyn/py_ad_B1n2_OLAF/AD.dat b/modules/aerodyn/py_ad_B1n2_OLAF/AD.dat new file mode 100644 index 000000000..d764e2b47 --- /dev/null +++ b/modules/aerodyn/py_ad_B1n2_OLAF/AD.dat @@ -0,0 +1,92 @@ +------- AERODYN v15 for OpenFAST INPUT FILE ----------------------------------------------- +NREL 5.0 MW offshore baseline aerodynamic input properties. +====== General Options ============================================================================ +False Echo - Echo the input to ".AD.ech"? (flag) +"default" DTAero - Time interval for aerodynamic calculations {or "default"} (s) + 3 WakeMod - Type of wake/induction model (switch) {0=none, 1=BEMT, 2=DBEMT, 3=OLAF} [WakeMod cannot be 2 or 3 when linearizing] + 1 AFAeroMod - Type of blade airfoil aerodynamics model (switch) {1=steady model, 2=Beddoes-Leishman unsteady model} [AFAeroMod must be 1 when linearizing] + 0 TwrPotent - Type tower influence on wind based on potential flow around the tower (switch) {0=none, 1=baseline potential flow, 2=potential flow with Bak correction} + 0 TwrShadow - Calculate tower influence on wind based on downstream tower shadow (switch) {0=none, 1=Powles model, 2=Eames model} +False TwrAero - Calculate tower aerodynamic loads? (flag) +False FrozenWake - Assume frozen wake during linearization? (flag) [used only when WakeMod=1 and when linearizing] +False CavitCheck - Perform cavitation check? (flag) [AFAeroMod must be 1 when CavitCheck=true] +False Buoyancy - Include buoyancy effects? (flag) +False CompAA - Flag to compute AeroAcoustics calculation [used only when WakeMod = 1 or 2] +"unused" AA_InputFile - AeroAcoustics input file [used only when CompAA=true] +====== Environmental Conditions =================================================================== +"default" AirDens - Air density (kg/m^3) +"default" KinVisc - Kinematic viscosity of working fluid (m^2/s) +"default" SpdSound - Speed of sound in working fluid (m/s) +"default" Patm - Atmospheric pressure (Pa) [used only when CavitCheck=True] +"default" Pvap - Vapour pressure of working fluid (Pa) [used only when CavitCheck=True] +====== Blade-Element/Momentum Theory Options ====================================================== [unused when WakeMod=0 or 3] + 2 SkewMod - Type of skewed-wake correction model (switch) {1=uncoupled, 2=Pitt/Peters, 3=coupled} [unused when WakeMod=0 or 3] +"default" SkewModFactor - Constant used in Pitt/Peters skewed wake model {or "default" is 15/32*pi} (-) [used only when SkewMod=2; unused when WakeMod=0 or 3] +True TipLoss - Use the Prandtl tip-loss model? (flag) [unused when WakeMod=0 or 3] +True HubLoss - Use the Prandtl hub-loss model? (flag) [unused when WakeMod=0 or 3] +True TanInd - Include tangential induction in BEMT calculations? (flag) [unused when WakeMod=0 or 3] +False AIDrag - Include the drag term in the axial-induction calculation? (flag) [unused when WakeMod=0 or 3] +False TIDrag - Include the drag term in the tangential-induction calculation? (flag) [unused when WakeMod=0,3 or TanInd=FALSE] +"Default" IndToler - Convergence tolerance for BEMT nonlinear solve residual equation {or "default"} (-) [unused when WakeMod=0 or 3] + 100 MaxIter - Maximum number of iteration steps (-) [unused when WakeMod=0] +====== Dynamic Blade-Element/Momentum Theory Options ============================================== [used only when WakeMod=2] + 3 DBEMT_Mod - Type of dynamic BEMT (DBEMT) model {1=constant tau1, 2=time-dependent tau1, 3=constant tau1 with continuous formulation} (-) [used only when WakeMod=2] + 100 tau1_const - Time constant for DBEMT (s) [used only when WakeMod=2 and DBEMT_Mod=1 or 3] +====== OLAF -- cOnvecting LAgrangian Filaments (Free Vortex Wake) Theory Options ================== [used only when WakeMod=3] +"OLAF.dat" OLAFInputFileName - Input file for OLAF [used only when WakeMod=3] +====== Beddoes-Leishman Unsteady Airfoil Aerodynamics Options ===================================== [used only when AFAeroMod=2] + 4 UAMod - Unsteady Aero Model Switch (switch) {2=B-L Gonzalez, 3=B-L Minnema/Pierce, 4=B-L HGM 4-states, 5=B-L 5 states, 6=Oye, 7=Boeing-Vertol} [used only when AFAeroMod=2] +True FLookup - Flag to indicate whether a lookup for f' will be calculated (TRUE) or whether best-fit exponential equations will be used (FALSE); if FALSE S1-S4 must be provided in airfoil input files (flag) [used only when AFAeroMod=2] +====== Airfoil Information ========================================================================= + 3 AFTabMod - Interpolation method for multiple airfoil tables {1=1D interpolation on AoA (first table only); 2=2D interpolation on AoA and Re; 3=2D interpolation on AoA and UserProp} (-) + 1 InCol_Alfa - The column in the airfoil tables that contains the angle of attack (-) + 2 InCol_Cl - The column in the airfoil tables that contains the lift coefficient (-) + 3 InCol_Cd - The column in the airfoil tables that contains the drag coefficient (-) + 4 InCol_Cm - The column in the airfoil tables that contains the pitching-moment coefficient; use zero if there is no Cm column (-) + 0 InCol_Cpmin - The column in the airfoil tables that contains the Cpmin coefficient; use zero if there is no Cpmin column (-) + 1 NumAFfiles - Number of airfoil files used (-) +"NACA64_A17.dat" AFNames - Airfoil file names (NumAFfiles lines) (quoted strings) +====== Rotor/Blade Properties ===================================================================== +True UseBlCm - Include aerodynamic pitching moment in calculations? (flag) +"AD_blade.dat" ADBlFile(1) - Name of file containing distributed aerodynamic properties for Blade #1 (-) +"AD_blade.dat" ADBlFile(2) - Name of file containing distributed aerodynamic properties for Blade #2 (-) [unused if NumBl < 2] +"AD_blade.dat" ADBlFile(3) - Name of file containing distributed aerodynamic properties for Blade #3 (-) [unused if NumBl < 3] +====== Hub Properties ============================================================================== [used only when Buoyancy=True] +0.0 VolHub - Hub volume (m^3) +0.0 HubCenBx - Hub center of buoyancy x direction offset (m) +====== Nacelle Properties ========================================================================== [used only when Buoyancy=True] +0.0 VolNac - Nacelle volume (m^3) +0,0,0 NacCenB - Position of nacelle center of buoyancy from yaw bearing in nacelle coordinates (m) +====== Tail fin Aerodynamics ======================================================================== +False TFinAero - Calculate tail fin aerodynamics model (flag) +"unused" TFinFile - Input file for tail fin aerodynamics [used only when TFinAero=True] +====== Tower Influence and Aerodynamics ============================================================ [used only when TwrPotent/=0, TwrShadow/=0, TwrAero=True, or Buoyancy=True] + 2 NumTwrNds - Number of tower nodes used in the analysis (-) [used only when TwrPotent/=0, TwrShadow/=0, TwrAero=True, or Buoyancy=True] +TwrElev TwrDiam TwrCd TwrTI TwrCb !TwrTI used only with TwrShadow=2, TwrCb used only with Buoyancy=True +(m) (m) (-) (-) (-) +0.0000000E+00 6.0000000E+00 1.0000000E+00 1.0000000E-01 0.0 +90.000000E+00 3.8700000E+00 1.0000000E+00 1.0000000E-01 0.0 +====== Outputs ==================================================================================== +False SumPrint - Generate a summary file listing input options and interpolated properties to ".AD.sum"? (flag) + 0 NBlOuts - Number of blade node outputs [0 - 9] (-) + 0 BlOutNd - Blade nodes whose values will be output (-) + 0 NTwOuts - Number of tower node outputs [0 - 9] (-) + 0 TwOutNd - Tower nodes whose values will be output (-) + OutList - The next line(s) contains a list of output parameters. See OutListParameters.xlsx for a listing of available output channels, (-) +END of input file (the word "END" must appear in the first 3 columns of this last OutList line) +---------------------- NODE OUTPUTS -------------------------------------------- + 1 BldNd_BladesOut - Blades to output + 99 BldNd_BlOutNd - Blade nodes on each blade (currently unused) + OutList - The next line(s) contains a list of output parameters. See OutListParameters.xlsx, AeroDyn_Nodes tab for a listing of available output channels, (-) +"VUndx" - x-component of undisturbed wind velocity at each node +"VUndy" - y-component of undisturbed wind velocity at each node +"VUndz" - z-component of undisturbed wind velocity at each node +"STVx" - x-component of structural translational velocity at each node +"STVy" - y-component of structural translational velocity at each node +"STVz" - z-component of structural translational velocity at each node +"VRel" - Relvative wind speed at each node +"Vindx" - Axial induced wind velocity at each node +"Vindy" - Tangential induced wind velocity at each node +"Alpha" - Angle of attack at each node +"Fn" - Normal force (to chord) per unit length at each node +"Ft" - Tangential force (to chord) per unit length at each node diff --git a/modules/aerodyn/py_ad_B1n2_OLAF/AD_blade.dat b/modules/aerodyn/py_ad_B1n2_OLAF/AD_blade.dat new file mode 100644 index 000000000..3201d4c95 --- /dev/null +++ b/modules/aerodyn/py_ad_B1n2_OLAF/AD_blade.dat @@ -0,0 +1,8 @@ +------- AERODYN v15.00.* BLADE DEFINITION INPUT FILE ------------------------------------- +Based on NREL 5 MW but with less stations +====== Blade Properties ================================================================= + 2 NumBlNds - Number of blade nodes used in the analysis (-) + BlSpn BlCrvAC BlSwpAC BlCrvAng BlTwist BlChord BlAFID BlCb BlCenBn BlCenBt + (m) (m) (m) (deg) (deg) (m) (-) (-) (m) (m) +0.0000000E+00 0.0000000E+00 0.0000000E+00 0.0000000E+00 0.0000000E+00 2.0000000E+00 1 0.0 0.0 0.0 +20.000000E+00 0.0000000E+00 0.0000000E+00 0.0000000E+00 0.0000000E+00 2.0000000E+00 1 0.0 0.0 0.0 diff --git a/modules/aerodyn/py_ad_B1n2_OLAF/NACA64_A17.dat b/modules/aerodyn/py_ad_B1n2_OLAF/NACA64_A17.dat new file mode 100644 index 000000000..b5193fd98 --- /dev/null +++ b/modules/aerodyn/py_ad_B1n2_OLAF/NACA64_A17.dat @@ -0,0 +1,181 @@ +! ------------ AirfoilInfo v1.01.x Input File ---------------------------------- +! NACA64 airfoil with an aspect ratio of 17. Original -180 to 180deg Cl, Cd, and Cm versus AOA data taken from Appendix A of DOWEC document 10046_009.pdf (numerical values obtained from Koert Lindenburg of ECN). +! Cl and Cd values corrected for rotational stall delay and Cd values corrected using the Viterna method for 0 to 90deg AOA by Jason Jonkman using AirfoilPrep_v2p0.xls. +! note that this file uses Marshall Buhl's new input file processing; start all comment lines with ! +! ------------------------------------------------------------------------------ +"DEFAULT" InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=1] + 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) +@"NACA64_A17_coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +"unused" BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. + 1 NumTabs ! Number of airfoil tables in this file. +! ------------------------------------------------------------------------------ +! data for table 1 +! ------------------------------------------------------------------------------ + 0.75 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ + -4.432 alpha0 ! 0-lift angle of attack, depends on airfoil. + 9 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) + -9 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] + 0 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] + 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 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] + 1.4073 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. + -0.7945 Cn2 ! As Cn1 for negative AOAs. + 0.19 St_sh ! Strouhal's shedding frequency constant. [default = 0.19] + 0.0065 Cd0 ! 2D drag coefficient value at 0-lift. + -0.088 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 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] + 0 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 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 ! Reduced frequency cut-off for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (-) [default = 0.5] +!........................................ +! Table of aerodynamics coefficients + 127 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) + -180.00 0.000 0.0198 0.0000 + -175.00 0.374 0.0341 0.1880 + -170.00 0.749 0.0955 0.3770 + -160.00 0.659 0.2807 0.2747 + -155.00 0.736 0.3919 0.3130 + -150.00 0.783 0.5086 0.3428 + -145.00 0.803 0.6267 0.3654 + -140.00 0.798 0.7427 0.3820 + -135.00 0.771 0.8537 0.3935 + -130.00 0.724 0.9574 0.4007 + -125.00 0.660 1.0519 0.4042 + -120.00 0.581 1.1355 0.4047 + -115.00 0.491 1.2070 0.4025 + -110.00 0.390 1.2656 0.3981 + -105.00 0.282 1.3104 0.3918 + -100.00 0.169 1.3410 0.3838 + -95.00 0.052 1.3572 0.3743 + -90.00 -0.067 1.3587 0.3636 + -85.00 -0.184 1.3456 0.3517 + -80.00 -0.299 1.3181 0.3388 + -75.00 -0.409 1.2765 0.3248 + -70.00 -0.512 1.2212 0.3099 + -65.00 -0.606 1.1532 0.2940 + -60.00 -0.689 1.0731 0.2772 + -55.00 -0.759 0.9822 0.2595 + -50.00 -0.814 0.8820 0.2409 + -45.00 -0.850 0.7742 0.2212 + -40.00 -0.866 0.6610 0.2006 + -35.00 -0.860 0.5451 0.1789 + -30.00 -0.829 0.4295 0.1563 + -25.00 -0.853 0.3071 0.1156 + -24.00 -0.870 0.2814 0.1040 + -23.00 -0.890 0.2556 0.0916 + -22.00 -0.911 0.2297 0.0785 + -21.00 -0.934 0.2040 0.0649 + -20.00 -0.958 0.1785 0.0508 + -19.00 -0.982 0.1534 0.0364 + -18.00 -1.005 0.1288 0.0218 + -17.00 -1.082 0.1037 0.0129 + -16.00 -1.113 0.0786 -0.0028 + -15.00 -1.105 0.0535 -0.0251 + -14.00 -1.078 0.0283 -0.0419 + -13.50 -1.053 0.0158 -0.0521 + -13.00 -1.015 0.0151 -0.0610 + -12.00 -0.904 0.0134 -0.0707 + -11.00 -0.807 0.0121 -0.0722 + -10.00 -0.711 0.0111 -0.0734 + -9.00 -0.595 0.0099 -0.0772 + -8.00 -0.478 0.0091 -0.0807 + -7.00 -0.375 0.0086 -0.0825 + -6.00 -0.264 0.0082 -0.0832 + -5.00 -0.151 0.0079 -0.0841 + -4.00 -0.017 0.0072 -0.0869 + -3.00 0.088 0.0064 -0.0912 + -2.00 0.213 0.0054 -0.0946 + -1.00 0.328 0.0052 -0.0971 + 0.00 0.442 0.0052 -0.1014 + 1.00 0.556 0.0052 -0.1076 + 2.00 0.670 0.0053 -0.1126 + 3.00 0.784 0.0053 -0.1157 + 4.00 0.898 0.0054 -0.1199 + 5.00 1.011 0.0058 -0.1240 + 6.00 1.103 0.0091 -0.1234 + 7.00 1.181 0.0113 -0.1184 + 8.00 1.257 0.0124 -0.1163 + 8.50 1.293 0.0130 -0.1163 + 9.00 1.326 0.0136 -0.1160 + 9.50 1.356 0.0143 -0.1154 + 10.00 1.382 0.0150 -0.1149 + 10.50 1.400 0.0267 -0.1145 + 11.00 1.415 0.0383 -0.1143 + 11.50 1.425 0.0498 -0.1147 + 12.00 1.434 0.0613 -0.1158 + 12.50 1.443 0.0727 -0.1165 + 13.00 1.451 0.0841 -0.1153 + 13.50 1.453 0.0954 -0.1131 + 14.00 1.448 0.1065 -0.1112 + 14.50 1.444 0.1176 -0.1101 + 15.00 1.445 0.1287 -0.1103 + 15.50 1.447 0.1398 -0.1109 + 16.00 1.448 0.1509 -0.1114 + 16.50 1.444 0.1619 -0.1111 + 17.00 1.438 0.1728 -0.1097 + 17.50 1.439 0.1837 -0.1079 + 18.00 1.448 0.1947 -0.1080 + 18.50 1.452 0.2057 -0.1090 + 19.00 1.448 0.2165 -0.1086 + 19.50 1.438 0.2272 -0.1077 + 20.00 1.428 0.2379 -0.1099 + 21.00 1.401 0.2590 -0.1169 + 22.00 1.359 0.2799 -0.1190 + 23.00 1.300 0.3004 -0.1235 + 24.00 1.220 0.3204 -0.1393 + 25.00 1.168 0.3377 -0.1440 + 26.00 1.116 0.3554 -0.1486 + 28.00 1.015 0.3916 -0.1577 + 30.00 0.926 0.4294 -0.1668 + 32.00 0.855 0.4690 -0.1759 + 35.00 0.800 0.5324 -0.1897 + 40.00 0.804 0.6452 -0.2126 + 45.00 0.793 0.7573 -0.2344 + 50.00 0.763 0.8664 -0.2553 + 55.00 0.717 0.9708 -0.2751 + 60.00 0.656 1.0693 -0.2939 + 65.00 0.582 1.1606 -0.3117 + 70.00 0.495 1.2438 -0.3285 + 75.00 0.398 1.3178 -0.3444 + 80.00 0.291 1.3809 -0.3593 + 85.00 0.176 1.4304 -0.3731 + 90.00 0.053 1.4565 -0.3858 + 95.00 -0.074 1.4533 -0.3973 + 100.00 -0.199 1.4345 -0.4075 + 105.00 -0.321 1.4004 -0.4162 + 110.00 -0.436 1.3512 -0.4231 + 115.00 -0.543 1.2874 -0.4280 + 120.00 -0.640 1.2099 -0.4306 + 125.00 -0.723 1.1196 -0.4304 + 130.00 -0.790 1.0179 -0.4270 + 135.00 -0.840 0.9064 -0.4196 + 140.00 -0.868 0.7871 -0.4077 + 145.00 -0.872 0.6627 -0.3903 + 150.00 -0.850 0.5363 -0.3665 + 155.00 -0.798 0.4116 -0.3349 + 160.00 -0.714 0.2931 -0.2942 + 170.00 -0.749 0.0971 -0.3771 + 175.00 -0.374 0.0334 -0.1879 + 180.00 0.000 0.0198 0.0000 diff --git a/modules/aerodyn/py_ad_B1n2_OLAF/NACA64_A17_coords.txt b/modules/aerodyn/py_ad_B1n2_OLAF/NACA64_A17_coords.txt new file mode 100644 index 000000000..aa31ac26b --- /dev/null +++ b/modules/aerodyn/py_ad_B1n2_OLAF/NACA64_A17_coords.txt @@ -0,0 +1,407 @@ + 400 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 +0.25 0 +! coordinates of airfoil shape; data from TU Delft as posted here: https://wind.nrel.gov/forum/wind/viewtopic.php?f=2&t=440 +! NACA 64-618 (interpolated to 399 points) +! x/c y/c +1.000000 0.000000 +0.990000 0.003385 +0.980000 0.006126 +0.975000 0.007447 +0.970000 0.008767 +0.965000 0.010062 +0.960000 0.011357 +0.955000 0.012639 +0.950000 0.013921 +0.945000 0.015200 +0.940000 0.016478 +0.935000 0.017757 +0.930000 0.019036 +0.925000 0.020317 +0.920000 0.021598 +0.915000 0.022881 +0.910000 0.024163 +0.905000 0.025448 +0.900000 0.026733 +0.887500 0.029951 +0.875000 0.033169 +0.862500 0.036386 +0.850000 0.039603 +0.837500 0.042804 +0.825000 0.046004 +0.812500 0.049171 +0.800000 0.052337 +0.787500 0.055452 +0.775000 0.058566 +0.762500 0.061611 +0.750000 0.064656 +0.737500 0.067615 +0.725000 0.070573 +0.712500 0.073429 +0.700000 0.076285 +0.687500 0.079029 +0.675000 0.081773 +0.662500 0.084393 +0.650000 0.087012 +0.637500 0.089490 +0.625000 0.091967 +0.612500 0.094283 +0.600000 0.096599 +0.587500 0.098743 +0.575000 0.100887 +0.562500 0.102843 +0.550000 0.104799 +0.537500 0.106549 +0.525000 0.108299 +0.512500 0.109830 +0.500000 0.111360 +0.487500 0.112649 +0.475000 0.113937 +0.462500 0.114964 +0.450000 0.115990 +0.445000 0.116320 +0.440000 0.116650 +0.435000 0.116931 +0.430000 0.117211 +0.425000 0.117439 +0.420000 0.117667 +0.415000 0.117835 +0.410000 0.118003 +0.405000 0.118104 +0.400000 0.118204 +0.395000 0.118231 +0.390000 0.118258 +0.385000 0.118213 +0.380000 0.118168 +0.375000 0.118057 +0.370000 0.117946 +0.365000 0.117777 +0.360000 0.117607 +0.355000 0.117383 +0.350000 0.117159 +0.345000 0.116881 +0.340000 0.116603 +0.335000 0.116273 +0.330000 0.115942 +0.325000 0.115562 +0.320000 0.115181 +0.315000 0.114750 +0.310000 0.114319 +0.305000 0.113838 +0.300000 0.113356 +0.295000 0.112824 +0.290000 0.112292 +0.285000 0.111710 +0.280000 0.111127 +0.275000 0.110495 +0.270000 0.109863 +0.265000 0.109180 +0.260000 0.108497 +0.255000 0.107762 +0.250000 0.107027 +0.245000 0.106241 +0.240000 0.105454 +0.235000 0.104614 +0.230000 0.103774 +0.225000 0.102880 +0.220000 0.101985 +0.215000 0.101035 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0.033454 +0.022500 0.031574 +0.020000 0.029694 +0.018750 0.028680 +0.017500 0.027666 +0.016250 0.026589 +0.015000 0.025511 +0.013750 0.024354 +0.012500 0.023197 +0.011250 0.021936 +0.010000 0.020674 +0.009500 0.020131 +0.009000 0.019587 +0.008500 0.019017 +0.008000 0.018447 +0.007500 0.017844 +0.007000 0.017241 +0.006500 0.016598 +0.006000 0.015955 +0.005500 0.015260 +0.005000 0.014565 +0.004500 0.013801 +0.004000 0.013037 +0.003500 0.012167 +0.003000 0.011296 +0.002500 0.010262 +0.002000 0.009227 +0.001875 0.008930 +0.001750 0.008633 +0.001625 0.008315 +0.001500 0.007997 +0.001375 0.007655 +0.001250 0.007312 +0.001125 0.006934 +0.001000 0.006555 +0.000875 0.006125 +0.000750 0.005695 +0.000625 0.005184 +0.000500 0.004672 +0.000400 0.004190 +0.000350 0.003913 +0.000300 0.003636 +0.000200 0.002970 +0.000100 0.002104 +0.000050 0.001052 +0.000000 0.000000 +0.000050 -0.001046 +0.000100 -0.002092 +0.000200 -0.002954 +0.000300 -0.003613 +0.000350 -0.003891 +0.000400 -0.004169 +0.000500 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-0.061163 +0.265000 -0.061354 +0.270000 -0.061545 +0.275000 -0.061708 +0.280000 -0.061871 +0.285000 -0.062004 +0.290000 -0.062137 +0.295000 -0.062240 +0.300000 -0.062343 +0.305000 -0.062417 +0.310000 -0.062490 +0.315000 -0.062534 +0.320000 -0.062577 +0.325000 -0.062590 +0.330000 -0.062602 +0.335000 -0.062583 +0.340000 -0.062563 +0.345000 -0.062512 +0.350000 -0.062460 +0.355000 -0.062374 +0.360000 -0.062287 +0.365000 -0.062164 +0.370000 -0.062040 +0.375000 -0.061878 +0.380000 -0.061716 +0.385000 -0.061509 +0.390000 -0.061301 +0.395000 -0.061040 +0.400000 -0.060778 +0.405000 -0.060458 +0.410000 -0.060138 +0.415000 -0.059763 +0.420000 -0.059388 +0.425000 -0.058966 +0.430000 -0.058544 +0.435000 -0.058083 +0.440000 -0.057622 +0.445000 -0.057127 +0.450000 -0.056632 +0.462500 -0.055265 +0.475000 -0.053897 +0.487500 -0.052374 +0.500000 -0.050850 +0.512500 -0.049195 +0.525000 -0.047539 +0.537500 -0.045777 +0.550000 -0.044014 +0.562500 -0.042165 +0.575000 -0.040316 +0.587500 -0.038401 +0.600000 -0.036486 +0.612500 -0.034526 +0.625000 -0.032565 +0.637500 -0.030575 +0.650000 -0.028585 +0.662500 -0.026594 +0.675000 -0.024603 +0.687500 -0.022632 +0.700000 -0.020660 +0.712500 -0.018728 +0.725000 -0.016795 +0.737500 -0.014922 +0.750000 -0.013048 +0.762500 -0.011260 +0.775000 -0.009472 +0.787500 -0.007797 +0.800000 -0.006122 +0.812500 -0.004594 +0.825000 -0.003065 +0.837500 -0.001721 +0.850000 -0.000376 +0.862500 0.000742 +0.875000 0.001859 +0.887500 0.002698 +0.900000 0.003536 +0.905000 0.003780 +0.910000 0.004023 +0.915000 0.004205 +0.920000 0.004387 +0.925000 0.004504 +0.930000 0.004620 +0.935000 0.004661 +0.940000 0.004702 +0.945000 0.004658 +0.950000 0.004614 +0.955000 0.004476 +0.960000 0.004338 +0.965000 0.004084 +0.970000 0.003829 +0.975000 0.003436 +0.980000 0.003042 +0.990000 0.001910 +1.000000 0.000000 diff --git a/modules/aerodyn/py_ad_B1n2_OLAF/OLAF.dat b/modules/aerodyn/py_ad_B1n2_OLAF/OLAF.dat new file mode 100644 index 000000000..0bbe81542 --- /dev/null +++ b/modules/aerodyn/py_ad_B1n2_OLAF/OLAF.dat @@ -0,0 +1,48 @@ +--------------------------- FREE WAKE INPUT FILE ---------------------------------------------- +Free wake input file for the BAR turbine +--------------------------- GENERAL OPTIONS --------------------------------------------------- +default IntMethod - Integration method {1: RK4, 5: Forward Euler 1st order, default: 5} (switch) +default DTfvw - Time interval for wake propagation. {default: dtaero} (s) +default FreeWakeStart - Time when wake is free. (-) value = always free. {default: 0.0} (s) +0.0 FullCircStart - Time at which full circulation is reached. {default: 0.0} (s) +-------------------------- CIRCULATION SPECIFICATIONS ---------------------------------------- +default CircSolvMethod - Circulation solving method {1: Cl-Based, 2: No-Flow Through, 3: Prescribed, default: 1 }(switch) +default CircSolvConvCrit - Convergence criteria {default: 0.001} [only if CircSolvMethod=1] (-) +default CircSolvRelaxation - Relaxation factor {default: 0.1} [only if CircSolvMethod=1] (-) +default CircSolvMaxIter - Maximum number of iterations for circulation solving {default: 30} (-) +"NA" PrescribedCircFile - File containing prescribed circulation [only if CircSolvMethod=3] (quoted string) +=============================================================================================== +--------------------------- WAKE OPTIONS ------------------------------------------------------ +------------------- WAKE EXTENT AND DISCRETIZATION -------------------------------------------- +100 nNWPanels - Number of near-wake panels (-) +default nNWPanelsFree - Number of free near-wake panels (-) {default: nNWPanels} +0 nFWPanels - Number of far-wake panels (-) {default: 0} +0 nFWPanelsFree - Number of free far-wake panels (-) {default: nFWPanels} +default FWShedVorticity - Include shed vorticity in the far wake {default: False} +------------------- WAKE REGULARIZATIONS AND DIFFUSION ----------------------------------------- +default DiffusionMethod - Diffusion method to account for viscous effects {0: None, 1: Core Spreading, "default": 0} +0 RegDeterMethod - Method to determine the regularization parameters {0: Manual, 1: Optimized, 2: Chord, 3: Span, default: 0 } +default RegFunction - Viscous diffusion function {0: None, 1: Rankine, 2: LambOseen, 3: Vatistas, 4: Denominator, "default": 3} (switch) +default WakeRegMethod - Wake regularization method {1: Constant, 2: Stretching, 3: Age, default: 3} (switch) +1.5 WakeRegFactor - Wake regularization factor (m or -) +1.5 WingRegFactor - Wing regularization factor (m or -) +1000 CoreSpreadEddyVisc - Eddy viscosity in core spreading methods, typical values 1-1000 +------------------- WAKE TREATMENT OPTIONS --------------------------------------------------- +False TwrShadowOnWake - Include tower flow disturbance effects on wake convection {default:false} [only if TwrPotent or TwrShadow] +default ShearModel - Shear Model {0: No treatment, 1: Mirrored vorticity, default: 0} +------------------- SPEEDUP OPTIONS ----------------------------------------------------------- +2 VelocityMethod - Method to determine the velocity {1:Segment N^2, 2:Particle tree, 3:Particle N^2, 4:Segment tree, default: 2} +default TreeBranchFactor - Branch radius fraction above which a multipole calculation is used {default: 1.5} [only if VelocityMethod=2,4] +default PartPerSegment - Number of particles per segment {default: 1} [only if VelocityMethod=2,3] +=============================================================================================== +--------------------------- OUTPUT OPTIONS --------------------------------------------------- +1 WrVTk - Outputs Visualization Toolkit (VTK) (independent of .fst option) {0: NoVTK, 1: Write VTK at VTK_fps, 2: Write VTK at init and final, default: 0} (flag) +0 nVTKBlades - Number of blades for which VTK files are exported {0: No VTK per blade, n: VTK for blade 1 to n, default: 0} (-) +1 VTKCoord - Coordinate system used for VTK export. {1: Global, 2: Hub, 3: Both, default: 1} +all VTK_fps - Frame rate for VTK output (frames per second) {"all" for all glue code timesteps, "default" for all OLAF timesteps} [only if WrVTK=1] +0 nGridOut - Number of grid outputs +GridName GridType TStart TEnd DTGrid XStart XEnd nX YStart YEnd nY ZStart ZEnd nZ +(-) (-) (s) (s) (s) (m) (m) (-) (m) (m) (-) (m) (m) (-) +=============================================================================================== +--------------------------- ADVANCED OPTIONS -------------------------------------------------- +=============================================================================================== diff --git a/modules/aerodyn/py_ad_B1n2_OLAF/README.md b/modules/aerodyn/py_ad_B1n2_OLAF/README.md new file mode 100644 index 000000000..44227f594 --- /dev/null +++ b/modules/aerodyn/py_ad_B1n2_OLAF/README.md @@ -0,0 +1,2 @@ +# One Rotating Blade with two aerodynamic section + diff --git a/modules/aerodyn/py_ad_B1n2_OLAF/ifw_primary.dat b/modules/aerodyn/py_ad_B1n2_OLAF/ifw_primary.dat new file mode 100644 index 000000000..1fae68786 --- /dev/null +++ b/modules/aerodyn/py_ad_B1n2_OLAF/ifw_primary.dat @@ -0,0 +1,71 @@ +------- InflowWind INPUT FILE ------------------------------------------------------------------------- +Steady 8 m/s winds with no shear for FAST CertTests #20 and #25 +--------------------------------------------------------------------------------------------------------------- +False Echo - Echo input data to .ech (flag) + 1 WindType - switch for wind file type (1=steady; 2=uniform; 3=binary TurbSim FF; 4=binary Bladed-style FF; 5=HAWC format; 6=User defined; 7=native Bladed FF) + 0 PropagationDir - Direction of wind propagation (meteorological rotation from aligned with X (positive rotates towards -Y) -- degrees) (not used for native Bladed format WindType=7) + 0 VFlowAng - Upflow angle (degrees) (not used for native Bladed format WindType=7) + False VelInterpCubic - Use cubic interpolation for velocity in time (false=linear, true=cubic) [Used with WindType=2,3,4,5,7] + 1 NWindVel - Number of points to output the wind velocity (0 to 9) + 0 WindVxiList - List of coordinates in the inertial X direction (m) + 0 WindVyiList - List of coordinates in the inertial Y direction (m) + 90 WindVziList - List of coordinates in the inertial Z direction (m) +================== Parameters for Steady Wind Conditions [used only for WindType = 1] ========================= + 2 HWindSpeed - Horizontal wind speed (m/s) + 90 RefHt - Reference height for horizontal wind speed (m) + 0.8 PLExp - Power law exponent (-) +================== Parameters for Uniform wind file [used only for WindType = 2] ============================ +"unused" Filename_Uni - Filename of time series data for uniform wind field. (-) + 90 RefHt_Uni - Reference height for horizontal wind speed (m) + 125.88 RefLength - Reference length for linear horizontal and vertical sheer (-) +================== Parameters for Binary TurbSim Full-Field files [used only for WindType = 3] ============== +"unused" FileName_BTS - Name of the Full field wind file to use (.bts) +================== Parameters for Binary Bladed-style Full-Field files [used only for WindType = 4 or WindType = 7] ========= +"unused" FileNameRoot - WindType=4: Rootname of the full-field wind file to use (.wnd, .sum); WindType=7: name of the intermediate file with wind scaling values +False TowerFile - Have tower file (.twr) (flag) ignored when WindType = 7 +================== Parameters for HAWC-format binary files [Only used with WindType = 5] ===================== +"wasp\Output\basic_5u.bin" FileName_u - name of the file containing the u-component fluctuating wind (.bin) +"wasp\Output\basic_5v.bin" FileName_v - name of the file containing the v-component fluctuating wind (.bin) +"wasp\Output\basic_5w.bin" FileName_w - name of the file containing the w-component fluctuating wind (.bin) + 64 nx - number of grids in the x direction (in the 3 files above) (-) + 32 ny - number of grids in the y direction (in the 3 files above) (-) + 32 nz - number of grids in the z direction (in the 3 files above) (-) + 16 dx - distance (in meters) between points in the x direction (m) + 3 dy - distance (in meters) between points in the y direction (m) + 3 dz - distance (in meters) between points in the z direction (m) + 90 RefHt_Hawc - reference height; the height (in meters) of the vertical center of the grid (m) + ------------- Scaling parameters for turbulence --------------------------------------------------------- + 1 ScaleMethod - Turbulence scaling method [0 = none, 1 = direct scaling, 2 = calculate scaling factor based on a desired standard deviation] + 1 SFx - Turbulence scaling factor for the x direction (-) [ScaleMethod=1] + 1 SFy - Turbulence scaling factor for the y direction (-) [ScaleMethod=1] + 1 SFz - Turbulence scaling factor for the z direction (-) [ScaleMethod=1] + 12 SigmaFx - Turbulence standard deviation to calculate scaling from in x direction (m/s) [ScaleMethod=2] + 8 SigmaFy - Turbulence standard deviation to calculate scaling from in y direction (m/s) [ScaleMethod=2] + 2 SigmaFz - Turbulence standard deviation to calculate scaling from in z direction (m/s) [ScaleMethod=2] + ------------- Mean wind profile parameters (added to HAWC-format files) --------------------------------- + 5 URef - Mean u-component wind speed at the reference height (m/s) + 2 WindProfile - Wind profile type (0=constant;1=logarithmic,2=power law) + 0 PLExp_Hawc - Power law exponent (-) (used for PL wind profile type only) + 0.03 Z0 - Surface roughness length (m) (used for LG wind profile type only) + 0 XOffset - Initial offset in +x direction (shift of wind box) +================== LIDAR Parameters =========================================================================== + 0 SensorType - Switch for lidar configuration (0 = None, 1 = Single Point Beam(s), 2 = Continuous, 3 = Pulsed) + 0 NumPulseGate - Number of lidar measurement gates (used when SensorType = 3) + 30 PulseSpacing - Distance between range gates (m) (used when SensorType = 3) + 0 NumBeam - Number of lidar measurement beams (0-5)(used when SensorType = 1) + -200 FocalDistanceX - Focal distance co-ordinates of the lidar beam in the x direction (relative to hub height) (only first coordinate used for SensorType 2 and 3) (m) + 0 FocalDistanceY - Focal distance co-ordinates of the lidar beam in the y direction (relative to hub height) (only first coordinate used for SensorType 2 and 3) (m) + 0 FocalDistanceZ - Focal distance co-ordinates of the lidar beam in the z direction (relative to hub height) (only first coordinate used for SensorType 2 and 3) (m) +0.0 0.0 0.0 RotorApexOffsetPos - Offset of the lidar from hub height (m) + 17 URefLid - Reference average wind speed for the lidar[m/s] + 0.25 MeasurementInterval - Time between each measurement [s] + False LidRadialVel - TRUE => return radial component, FALSE => return 'x' direction estimate + 1 ConsiderHubMotion - Flag whether to consider the hub motion's impact on Lidar measurements +====================== OUTPUT ================================================== +False SumPrint - Print summary data to .IfW.sum (flag) + OutList - The next line(s) contains a list of output parameters. See OutListParameters.xlsx for a listing of available output channels, (-) +"Wind1VelX" X-direction wind velocity at point WindList(1) +"Wind1VelY" Y-direction wind velocity at point WindList(1) +"Wind1VelZ" Z-direction wind velocity at point WindList(1) +END of input file (the word "END" must appear in the first 3 columns of this last OutList line) +--------------------------------------------------------------------------------------- diff --git a/modules/aerodyn/py_ad_B1n2_OLAF/py_ad_driver.out b/modules/aerodyn/py_ad_B1n2_OLAF/py_ad_driver.out new file mode 100644 index 000000000..c2cbdffb5 --- /dev/null +++ b/modules/aerodyn/py_ad_B1n2_OLAF/py_ad_driver.out @@ -0,0 +1,68 @@ +## This file was generated by AeroDyn_Inflow_Driver on Sep-26-2023 at 11:38:46 +## This file contains output channels requested from the OutList section of the AD15 and IfW input filespy_ad_driver.out +# +# +# +# + Time AB1N001VUndx AB1N002VUndx AB1N001VUndy AB1N002VUndy AB1N001VUndz AB1N002VUndz AB1N001STVx AB1N002STVx AB1N001STVy AB1N002STVy AB1N001STVz AB1N002STVz AB1N001VRel AB1N002VRel AB1N001Vindx AB1N002Vindx AB1N001Vindy AB1N002Vindy AB1N001Alpha AB1N002Alpha AB1N001Fn AB1N002Fn AB1N001Ft AB1N002Ft Wind1VelX Wind1VelY Wind1VelZ + (s) (m/s) (m/s) (m/s) (m/s) (m/s) (m/s) (m/s) (m/s) (m/s) (m/s) (m/s) (m/s) (m/s) (m/s) (m/s) (m/s) (m/s) (m/s) (deg) (deg) (N/m) (N/m) (N/m) (N/m) (m/s) (m/s) (m/s) + 0.0000 2.1669447 2.5060766 0.0000000 0.0000000 0.1895932 0.2192650 0.0000000 0.0000000 -10.4719801 -31.4159336 0.0000000 0.0000000 10.6938305 31.5157318 0.0000000 0.0000000 0.0000000 0.0000000 11.6910906 4.5608768 197.4951172 1166.5699463 33.1142960 86.1932983 2.0000000 -0.0000000 0.0000000 + 0.1000 2.1659980 2.5033383 0.0198096 0.0228948 0.1884722 0.2178256 0.0000071 0.0000122 -10.4719763 -31.4159336 0.0000224 0.0000567 10.6268654 31.5374527 -0.8776832 -0.8776832 0.0566991 0.0566991 6.9631643 2.9547019 161.9676208 948.0039673 18.2178745 42.4651566 2.0000000 -0.0000000 0.0000000 + 0.2000 2.1631684 2.4951491 0.0393496 0.0453885 0.1851271 0.2135385 0.0000095 0.0000286 -10.4719782 -31.4159279 -0.0000211 -0.0000651 10.6686573 31.5660801 -0.6656135 -0.6656135 0.0517029 0.0517029 8.0691805 3.3226111 174.4599762 1000.5437012 22.9756889 51.5675812 2.0000000 -0.0000000 0.0000000 + 0.3000 2.1584849 2.4815853 0.0583591 0.0670948 0.1796098 0.2064954 0.0000123 0.0000476 -10.4719744 -31.4159298 0.0000226 0.0000591 10.6966228 31.5878849 -0.5620127 -0.5620127 0.0464835 0.0464835 8.5834055 3.4838827 180.2362366 1024.2086182 25.3478470 55.8046722 2.0000000 -0.0000000 0.0000000 + 0.4000 2.1519957 2.4627740 0.0765827 0.0876424 0.1720071 0.1968473 0.0000156 0.0000558 -10.4719810 -31.4159317 0.0000124 0.0000438 10.7193069 31.6072197 -0.4996090 -0.4996090 0.0426225 0.0426225 8.8674469 3.5609052 183.4877014 1036.1123047 26.7118206 57.9094849 2.0000000 -0.0000000 0.0000000 + 0.5000 2.1437678 2.4388916 0.0937823 0.1066930 0.1624366 0.1847986 0.0000205 0.0000722 -10.4719772 -31.4159298 -0.0000199 -0.0000723 10.7386198 31.6244888 -0.4585096 -0.4585096 0.0398017 0.0398017 9.0288877 3.5901823 185.5399475 1041.2962646 27.5314579 58.7552567 2.0000000 -0.0000000 0.0000000 + 0.6000 2.1338866 2.4101629 0.1097403 0.1239485 0.1510440 0.1705998 0.0000260 0.0000879 -10.4719782 -31.4159317 0.0000241 0.0000669 10.7553129 31.6396084 -0.4293512 -0.4293512 0.0376690 0.0376690 9.1187220 3.5892158 186.8306580 1042.1583252 28.0123463 58.7855301 2.0000000 -0.0000000 0.0000000 + 0.7000 2.1224551 2.3768609 0.1242584 0.1391525 0.1380022 0.1545436 0.0000337 0.0001002 -10.4719753 -31.4159317 0.0000227 0.0000832 10.7695990 31.6523952 -0.4079521 -0.4079521 0.0360213 0.0360213 9.1601906 3.5661530 187.6572571 1039.8038330 28.2705193 58.2153397 2.0000000 -0.0000000 0.0000000 + 0.8000 2.1095920 2.3393023 0.1371658 0.1521016 0.1235053 0.1369537 0.0000390 0.0001071 -10.4719753 -31.4159317 -0.0000282 -0.0000849 10.7816296 31.6626778 -0.3911102 -0.3911102 0.0346593 0.0346593 9.1712694 3.5274210 188.1650848 1035.1059570 28.3829918 57.2209015 2.0000000 -0.0000000 0.0000000 + 0.9000 2.0954323 2.2978492 0.1483220 0.1626498 0.1077627 0.1181725 0.0000435 0.0001197 -10.4719753 -31.4159298 -0.0000251 -0.0000622 10.7913666 31.6703262 -0.3777477 -0.3777477 0.0334954 0.0334954 9.1586123 3.4756303 188.4040222 1028.4161377 28.3778877 55.8789940 2.0000000 -0.0000000 0.0000000 + 1.0000 2.0801244 2.2529032 0.1576143 0.1707060 0.0909982 0.0985566 0.0000376 0.0001221 -10.4719801 -31.4159298 0.0000242 0.0000686 10.7989426 31.6753178 -0.3659256 -0.3659256 0.0324328 0.0324328 9.1334314 3.4150534 188.4672394 1020.3256836 28.3055401 54.3107491 2.0000000 -0.0000000 0.0000000 + 1.1000 2.0638306 2.2049055 0.1649601 0.1762361 0.0734452 0.0784656 0.0000407 0.0001329 -10.4719753 -31.4159355 -0.0000089 -0.0000384 10.8043098 31.6776752 -0.3556045 -0.3556045 0.0314858 0.0314858 9.0967598 3.3465142 188.3608856 1010.9530029 28.1704350 52.5458107 2.0000000 -0.0000000 0.0000000 + 1.2000 2.0467236 2.1543324 0.1703101 0.1792643 0.0553374 0.0582469 0.0000486 0.0001366 -10.4719744 -31.4159355 -0.0000166 -0.0000528 10.8074865 31.6774406 -0.3463546 -0.3463546 0.0306101 0.0306101 9.0518389 3.2716653 188.1114349 1000.5335083 27.9874420 50.6349220 2.0000000 -0.0000000 0.0000000 + 1.3000 2.0289865 2.1016929 0.1736436 0.1798659 0.0369087 0.0382313 0.0000459 0.0001477 -10.4719763 -31.4159336 0.0000262 0.0000691 10.8084917 31.6747074 -0.3379403 -0.3379403 0.0297728 0.0297728 9.0009642 3.1918023 187.7381592 989.2577515 27.7672997 48.6185417 2.0000000 -0.0000000 0.0000000 + 1.4000 2.0108092 2.0475240 0.1749686 0.1781633 0.0183902 0.0187260 0.0000515 0.0001438 -10.4719772 -31.4159260 -0.0000177 -0.0000522 10.8073759 31.6696434 -0.3301869 -0.3301869 0.0289645 0.0289645 8.9459229 3.1082194 187.2118835 977.3209839 27.5099087 46.5357628 2.0000000 -0.0000000 0.0000000 + 1.5000 1.9923886 1.9923885 0.1743207 0.1743207 0.0000000 0.0000000 0.0000518 0.0001444 -10.4719782 -31.4159317 -0.0000000 -0.0000000 10.8042259 31.6624641 -0.3229573 -0.3229573 0.0281779 0.0281779 8.8884792 3.0221100 186.5930786 964.9075928 27.2322445 44.4214554 2.0000000 -0.0000000 0.0000000 + 1.6000 1.9739254 1.9368688 0.1717592 0.1685348 -0.0180529 -0.0177140 0.0000515 0.0001438 -10.4719772 -31.4159260 0.0000177 0.0000522 10.7991276 31.6533813 -0.3162481 -0.3162481 0.0274131 0.0274131 8.8295946 2.9345076 185.8946991 952.1793823 26.9397049 42.2966728 2.0000000 -0.0000000 0.0000000 + 1.7000 1.9556220 1.8815628 0.1673650 0.1610269 -0.0355741 -0.0342270 0.0000459 0.0001477 -10.4719763 -31.4159336 -0.0000262 -0.0000691 10.7922096 31.6426697 -0.3099540 -0.3099540 0.0266654 0.0266654 8.7708139 2.8466353 185.1355133 939.3271484 26.6402569 40.1984749 2.0000000 -0.0000000 0.0000000 + 1.8000 1.9376805 1.8270800 0.1612365 0.1520333 -0.0523892 -0.0493989 0.0000486 0.0001366 -10.4719744 -31.4159355 0.0000166 0.0000528 10.7835932 31.6305866 -0.3040951 -0.3040951 0.0259375 0.0259375 8.7129087 2.7595606 184.3272095 926.5179443 26.3382378 38.1555595 2.0000000 -0.0000000 0.0000000 + 1.9000 1.9203001 1.7740326 0.1534879 0.1417968 -0.0683374 -0.0631322 0.0000407 0.0001329 -10.4719753 -31.4159355 0.0000089 0.0000384 10.7734337 31.6173992 -0.2986646 -0.2986646 0.0252315 0.0252315 8.6569424 2.6743326 183.4849854 913.9161377 26.0392952 36.1915016 2.0000000 -0.0000000 0.0000000 + 2.0000 1.9036756 1.7230320 0.1442445 0.1305568 -0.0832791 -0.0753766 0.0000376 0.0001221 -10.4719801 -31.4159298 -0.0000242 -0.0000686 10.7618828 31.6033745 -0.2936659 -0.2936659 0.0245518 0.0245518 8.6037169 2.5920520 182.6216583 901.6918335 25.7477932 34.3290749 2.0000000 -0.0000000 0.0000000 + 2.1000 1.8879942 1.6746798 0.1336388 0.1185397 -0.0970947 -0.0861245 0.0000435 0.0001197 -10.4719753 -31.4159298 0.0000251 0.0000622 10.7490883 31.5887680 -0.2891080 -0.2891080 0.0239017 0.0239017 8.5540400 2.5137424 181.7497559 890.0026855 25.4679565 32.5874481 2.0000000 -0.0000000 0.0000000 + 2.2000 1.8734344 1.6295612 0.1218108 0.1059542 -0.1096796 -0.0954021 0.0000390 0.0001071 -10.4719753 -31.4159317 0.0000282 0.0000849 10.7352314 31.5738087 -0.2850096 -0.2850096 0.0232863 0.0232863 8.5087290 2.4404500 180.8828125 879.0064697 25.2040901 30.9846764 2.0000000 -0.0000000 0.0000000 + 2.3000 1.8601619 1.5882359 0.1089025 0.0929827 -0.1209478 -0.1032672 0.0000337 0.0001002 -10.4719753 -31.4159317 -0.0000227 -0.0000832 10.7204752 31.5586910 -0.2813511 -0.2813511 0.0227092 0.0227092 8.4686041 2.3731861 180.0074463 868.8533936 24.9564095 29.5366631 2.0000000 -0.0000000 0.0000000 + 2.4000 1.8483297 1.5512296 0.0950549 0.0797758 -0.1308312 -0.1098014 0.0000260 0.0000879 -10.4719782 -31.4159317 -0.0000241 -0.0000669 10.7049837 31.5435791 -0.2781731 -0.2781731 0.0221763 0.0221763 8.4341631 2.3128490 179.1572876 859.6749878 24.7311172 28.2559280 2.0000000 -0.0000000 0.0000000 + 2.5000 1.8380742 1.5190235 0.0804093 0.0664520 -0.1392737 -0.1150988 0.0000205 0.0000722 -10.4719772 -31.4159298 0.0000199 0.0000723 10.6889086 31.5286045 -0.2754822 -0.2754822 0.0216921 0.0216921 8.4059782 2.2602973 178.3500824 851.5949097 24.5321922 27.1536274 2.0000000 -0.0000000 0.0000000 + 2.6000 1.8295146 1.4920471 0.0651067 0.0530973 -0.1462315 -0.1192580 0.0000156 0.0000558 -10.4719810 -31.4159317 -0.0000124 -0.0000438 10.6724186 31.5138683 -0.2733185 -0.2733185 0.0212654 0.0212654 8.3843784 2.2162378 177.5942230 844.7136230 24.3614635 26.2376900 2.0000000 -0.0000000 0.0000000 + 2.7000 1.8227509 1.4706663 0.0492819 0.0397625 -0.1516730 -0.1223757 0.0000123 0.0000476 -10.4719744 -31.4159298 -0.0000226 -0.0000591 10.6556501 31.4994183 -0.2716808 -0.2716808 0.0209021 0.0209021 8.3698254 2.1813316 176.8982086 839.1218262 24.2211933 25.5153828 2.0000000 -0.0000000 0.0000000 + 2.8000 1.8178623 1.4551761 0.0330682 0.0264707 -0.1555753 -0.1245361 0.0000095 0.0000286 -10.4719782 -31.4159279 0.0000211 0.0000651 10.6387711 31.4852962 -0.2705730 -0.2705730 0.0206075 0.0206075 8.3626337 2.1561539 176.2700500 834.8976440 24.1131268 24.9929657 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http://www.apache.org/licenses/LICENSE-2.0 +# +# Unless required by applicable law or agreed to in writing, software +# distributed under the License is distributed on an "AS IS" BASIS, +# WITHOUT WARRANTIES OR CONDITIONS OF ANY KIND, either express or implied. +# See the License for the specific language governing permissions and +# limitations under the License. +# +#******************************************************************************* +# +# This is an exampe of Python driver code for AeroDyn with InflowWind +# +# Usage: This program gives an example for how the user calls the main +# subroutines of AeroDyn, and thus is specific to the user +# +# Basic alogrithm for using AeroDyn InflowWind python library +# 1. initialize python wrapper library +# set necessary library values +# set input file string arrays (from file or script) +# 2. initialize AeroDyn Fortran library +# - ADI_PreInit -- set number of turbines +# - ADI_SetupTurb -- initialize one rotor (iterate over turbines) +# - ADI_Init -- actually call ADI to initialize the simulation +# 3. timestep iteration +# - ADI_SetMotion -- set motions of single turbine (iterate over turbines) +# - ADI_UpdateStates -- update to next timestep +# - ADI_CalcOutput -- get outputs +# - ADI_GetRotorLoads -- get loads per rotor (iterate over turbines) +# 4. End +# call adi_end to close the AeroDyn library and free memory +# handle any resulting errors +# +# +import numpy as np +import os +import sys +from visread import * + +# path to find the aerodyn_inflow_library.py from the local directory +os.chdir(sys.path[0]) +adiLibPath=os.path.sep.join(["..", "..", "..", "..", "..", "modules", "aerodyn", "python-lib"]) +sys.path.insert(0, adiLibPath) +print(f"Importing 'aerodyn_inflow_library' from {adiLibPath}") +import aerodyn_inflow_library as adi # this file handles the conversion from python to c-bound types and should not be changed by the user + +############################################################################### +# Locations to build directory relative to r-test directory. This is specific +# to the regession testing with openfast and will need to be updated when +# coupled to other codes or use cases + +basename = "libaerodyn_inflow_c_binding" +builddir=os.path.sep.join(["..", "..", "..", "..", "..", "build"]) +if sys.platform == "linux" or sys.platform == "linux2": + library_path = os.path.sep.join([builddir, "modules", "aerodyn", basename + ".so"]) +elif sys.platform == "darwin": + library_path = os.path.sep.join([builddir, "modules", "aerodyn", basename + ".dylib"]) +elif sys.platform == "win32": + # Windows may have this library installed in one of two locations depending + # on which build system was used (CMake or VS). + library_path = os.path.sep.join([builddir, "modules", "aerodyn", basename + ".dll"]) # cmake install location + if not os.path.isfile(library_path) and not sys.maxsize > 2**32: # Try VS build location otherwise + library_path = os.path.sep.join([builddir, "bin", "AeroDyn_Inflow_c_binding_Win32.dll"]) # VS build install location + if not os.path.isfile(library_path): + print(f"Python is 32 bit and cannot find 32 bit InflowWind DLL expected at: {library_path}") + exit(1) + if not os.path.isfile(library_path) and sys.maxsize > 2**32: # Try VS build location otherwise + library_path = os.path.sep.join([builddir, "bin", "AeroDyn_Inflow_c_binding_x64.dll"]) # VS build install location + if not os.path.isfile(library_path): + print(f"Python is 64 bit and cannot find 64 bit InflowWind DLL expected at: {library_path}") + exit(1) + + + +############################################################################### +# For testing, a set of input files is read in. Everything in these input +# files could in principle be hard coded into this script. These are separated +# out for convenience in testing. + +# Primary input +# This is identical to what AeroDyn would read from disk if we were +# not passing it. When coupled to other codes, this may be passed +# directly from memory (i.e. during optimization with WEIS), or read as a +# template and edited in memory for each iteration loop. +primary_ad_file="AD.dat" +primary_ifw_file="ifw_primary.dat" + +# Debug output file +# When coupled into another code, an array of position/orientation, +# velocities, and accelerations are passed in, and an array of +# Forces+Moments is returned. For debugging, it may be useful to dump all +# off this to file. +DbgOuts=0 # For checking the interface, set this to 1 +debugout_file="DbgOutputs.out" + +# Output file +# When coupled to another code, the channels requested in the outlist +# section of the output file are passed back for writing to file. Here +# we will write the aggregated output channels to a file at the end of +# the simulation. +output_file="py_ad_driver.out" + +# For checking if our library is correctly handling correction steps, set +# this to > 0 +NumCorrections=0 + + +#=============================================================================== +# Mesh inputs from vtk +vtkDir="vtkRef" +numBlades=1 +vtkFieldLen=9 +TimeStepsToRun=59 +hubMeshRootName="AD_HubMotion" +nacMeshRootName="AD_Nacelle" +bldRootMeshRootName="AD_BladeRootMotion" +bldMeshRootName="AD_BladeMotion" # for struct mesh not aligned with AD15 mesh + + + +# Input Files +#=============================================================================== +# Main AeroDyn input file +# This file is read from disk to an array of strings with the line +# endings stripped off. This array will have the same number of elements +# as there are lines in the file. +adiAD_input_string_array = [] # instantiate empty array +fh = open(primary_ad_file, "r") +for line in fh: + # strip line ending and ending white space and add to array of strings + adiAD_input_string_array.append(line.rstrip()) +fh.close() + +adiIfW_input_string_array = [] # instantiate empty array +fh = open(primary_ifw_file, "r") +for line in fh: + # strip line ending and ending white space and add to array of strings + adiIfW_input_string_array.append(line.rstrip()) +fh.close() + + +#=============================================================================== +# Number of turbines +numTurbines = 1 + +#=============================================================================== +# Initial hub and root locations from vtk files +# can add checks here that numpts==1 +initHubPos, initHubOrient, numpts = visread_positions_ref(os.path.sep.join([vtkDir, hubMeshRootName+"_Reference.vtp"])) +initNacellePos, initNacelleOrient, numpts = visread_positions_ref(os.path.sep.join([vtkDir, nacMeshRootName+"_Reference.vtp"])) + +initRootPos = np.zeros((numBlades,3),dtype="float32") +initRootOrient = np.zeros((numBlades,9),dtype="float64") +for i in range(numBlades): + # can add checks here that numpts==1 + initRootPos[i,:], initRootOrient[i,:], numpts = visread_positions_ref(os.path.sep.join([vtkDir, bldRootMeshRootName+str(i+1)+"_Reference.vtp"])) + +# Initial blade mesh positions +numBladeNode = np.zeros( (numBlades), dtype=int ) +initMeshPos_ar = np.empty( (0,3), dtype="float32" ) +initMeshOrient_ar = np.empty( (0,9), dtype="float64" ) +for i in range(numBlades): + # can add checks here that numpts==1 + tmpPos, tmpOrient, numpts = visread_positions_ref(os.path.sep.join([vtkDir, bldMeshRootName+str(i+1)+"_Reference.vtp"])) + initMeshPos_ar = np.concatenate((initMeshPos_ar, tmpPos )) + initMeshOrient_ar = np.concatenate((initMeshOrient_ar,tmpOrient)) + numBladeNode[i] = numpts +del tmpPos +del tmpOrient + +#=============================================================================== +# Helper functions +#=============================================================================== +def SetMotionHub(N_Step): + timeField=str(N_Step).zfill(vtkFieldLen) + HubPos, HubOrient, numpts = visread_positions(os.path.sep.join([vtkDir, hubMeshRootName+'.'+timeField+".vtp"])) + HubVel, HubAcc = visread_velacc( os.path.sep.join([vtkDir, hubMeshRootName+'.'+timeField+".vtp"]),numpts) + return (HubPos, HubOrient, HubVel, HubAcc) + +def SetMotionNac(N_Step): + timeField=str(N_Step).zfill(vtkFieldLen) + NacPos, NacOrient, numpts = visread_positions(os.path.sep.join([vtkDir, nacMeshRootName+'.'+timeField+".vtp"])) + NacVel, NacAcc = visread_velacc( os.path.sep.join([vtkDir, nacMeshRootName+'.'+timeField+".vtp"]),numpts) + return (NacPos, NacOrient, NacVel, NacAcc) + +def SetMotionRoot(N_Step): + timeField=str(N_Step).zfill(vtkFieldLen) + RootPos = np.zeros((numBlades,3),dtype="float32") + RootOrient = np.zeros((numBlades,9),dtype="float64") + RootVel = np.zeros((numBlades,6),dtype="float32") + RootAcc = np.zeros((numBlades,6),dtype="float32") + for k in range(numBlades): + RootPos[k,:], RootOrient[k,:], numpts = visread_positions(os.path.sep.join([vtkDir, bldRootMeshRootName+str(k+1)+'.'+timeField+".vtp"])) + RootVel[k,:], RootAcc[k,:] = visread_velacc( os.path.sep.join([vtkDir, bldRootMeshRootName+str(k+1)+'.'+timeField+".vtp"]),numpts) + return (RootPos, RootOrient, RootVel, RootAcc) + +def SetMotionBlMesh(N_Step): + timeField=str(N_Step).zfill(vtkFieldLen) + MeshPos_ar = np.empty( (0,3), dtype="float32" ) + MeshOrient_ar = np.empty( (0,9), dtype="float64" ) + MeshVel_ar = np.empty( (0,6), dtype="float32" ) + MeshAcc_ar = np.empty( (0,6), dtype="float32" ) + MeshFrcMom = np.zeros((sum(numBladeNode),6)) # [Fx,Fy,Fz,Mx,My,Mz] -- resultant forces/moments at each node + for k in range(numBlades): + tmpPos, tmpOrient, numpts = visread_positions(os.path.sep.join([vtkDir, bldMeshRootName+str(k+1)+'.'+timeField+".vtp"])) + tmpVel, tmpAcc = visread_velacc( os.path.sep.join([vtkDir, bldMeshRootName+str(k+1)+'.'+timeField+".vtp"]),numpts) + MeshPos_ar = np.concatenate((MeshPos_ar, tmpPos )) + MeshOrient_ar = np.concatenate((MeshOrient_ar,tmpOrient)) + MeshVel_ar = np.concatenate((MeshVel_ar, tmpVel )) + MeshAcc_ar = np.concatenate((MeshAcc_ar, tmpAcc )) + del tmpPos + del tmpOrient + del tmpVel + del tmpAcc + return (MeshPos_ar, MeshOrient_ar, MeshVel_ar, MeshAcc_ar, MeshFrcMom) + +#=============================================================================== +# AeroDyn python interface initialization +#=============================================================================== + +# Instantiate the hdlib python object +# wrap this in error handling in case the library_path is incorrect +try: + adilib = adi.AeroDynInflowLib(library_path) +except Exception as e: + print("{}".format(e)) + print(f"Cannot load library at {library_path}") + exit(1) + +# These will be read from the AD driver input file +# Time inputs +# adlib.dt -- the timestep aerodyn is called at. +# adlib.numTimeSteps -- total number of timesteps, only used to +# construct arrays to hold the output channel +# info +adilib.InterpOrder = 2 # order of the interpolation +adilib.dt = 0.1 # time interval that it's being called at +final_time = 5.9 # final time +adilib.gravity = 9.80665 # Gravitational acceleration (m/s^2) +adilib.defFldDens = 1.225 # Air density (kg/m^3) +adilib.defKinVisc = 1.464E-05 # Kinematic viscosity of working fluid (m^2/s) +adilib.defSpdSound = 335.0 # Speed of sound in working fluid (m/s) +adilib.defPatm = 103500.0 # Atmospheric pressure (Pa) [used only for an MHK turbine cavitation check] +adilib.defPvap = 1700.0 # Vapour pressure of working fluid (Pa) [used only for an MHK turbine cavitation check] +adilib.WtrDpth = 0.0 # Water depth (m) +adilib.MSL2SWL = 0.0 # Offset between still-water level and mean sea level (m) [positive upward] +adilib.numTurbines = numTurbines + +# Setup some timekeeping -- this may be smaller than what is passed to AD15 +adilib.numTimeSteps = TimeStepsToRun # only for constructing array of output channels for duration of simulation +time = np.arange(0.0,(TimeStepsToRun+1)*adilib.dt,adilib.dt) # total time + increment because python doesnt include endpoint! + +# set some flags +adilib.storeHHvel = False +adilib.WrVTK = 0 # animation (0: off, 1: init only, 2: all timesteps) +adilib.WrVTK_Type = 3 # surface and line meshes +adilib.transposeDCM = 1 # 0=false, 1=true + +#============================================================================== +# Basic alogrithm for using AeroDyn+InflowWind library +# +# NOTE: the error handling here is handled locally since this is the only +# driver code. If AeroDyn+InflowWind is incorporated into another code, +# the error handling will need to be passed to the main code. That way +# the main code can close other modules as necessary (otherwise you will +# end up with memory leaks and a bunch of garbage in the other library +# instances). + +isHAWT = 0 # 1: HAWT, 0: VAWT or cross-flow + +# Set hub and blade root positions/orientations +adilib.initHubPos = initHubPos[0,:] +adilib.initHubOrient = initHubOrient[0,:] +adilib.initNacellePos = initNacellePos[0,:] +adilib.initNacelleOrient = initNacelleOrient[0,:] +adilib.numBlades = numBlades +#adilib.numBladeNode = numBladeNode # May be necessary to pass info on nodes on each blade to AD15 for mesh mapping. +adilib.initRootPos = initRootPos +adilib.initRootOrient = initRootOrient + + +# Set number of mesh nodes and initial position +# position is an N x 3 array [x,y,z] +# orientation is a N x 9 array [r11,r12,r13,r21,r22,r23,r31,r32,r33] +adilib.numMeshPts = np.size(initMeshPos_ar,0) +adilib.initMeshPos = initMeshPos_ar +adilib.initMeshOrient = initMeshOrient_ar + +# ADI_PreInit: call before anything else +try: + adilib.adi_preinit() +except Exception as e: + print("{}".format(e)) # Exceptions handled in adi_library.py + #FIXME: temporary statement here + print("Exit after failed call to adi_preinit") + exit(1) + +# ADI_SetupRotor +try: + #FIXME: hard code to one turbine for now + iturb=1 + turbRefPos=[0,0,0] + adilib.adi_setuprotor(iturb,isHAWT,turbRefPos) +except Exception as e: + print("{}".format(e)) # Exceptions handled in adi_library.py + #FIXME: temporary statement here + print("Exit after failed call to adi_setuprotor") + exit(1) + +# ADI_Init: Only need to call adi_init once +try: + adilib.adi_init(adiAD_input_string_array,adiIfW_input_string_array) +except Exception as e: + print("{}".format(e)) # Exceptions handled in adi_library.py + #FIXME: temporary statement here + print("Exit after failed call to adi_init") + exit(1) + + +# To get the names and units of the output channels +output_channel_names = adilib.output_channel_names +output_channel_units = adilib.output_channel_units + + +#------------------- +# Time steppping +#------------------- + +# Set the array holding the ouput channel values to zeros initially. Output +# channel values returned from each CalcOutput call in this array. We will +# aggregate them together in the time stepping loop to get the entire time +# series. Time channel is not included, so we must add that. +outputChannelValues = np.zeros(adilib.numChannels) +allOutputChannelValues = np.zeros( (adilib.numTimeSteps+1,adilib.numChannels+1) ) + +# Open outputfile for regession testing purposes. +if DbgOuts == 1: + dbg_outfile = adi.DriverDbg(debugout_file,adilib.numMeshPts) + +#-------------------------------- +# Calculate outputs for t_initial +i=0 +# read position/motion from vtk +HubPos, HubOrient, HubVel, HubAcc = SetMotionHub(i) +NacPos, NacOrient, NacVel, NacAcc = SetMotionNac(i) +RootPos, RootOrient, RootVel, RootAcc = SetMotionRoot(i) +MeshPos_ar, MeshOrient_ar, MeshVel_ar, MeshAcc_ar, MeshFrcMom = SetMotionBlMesh(i) + +# Set initial motions for rotor 1 +try: + adilib.adi_setrotormotion( + iturb, + HubPos, HubOrient, HubVel, HubAcc, + NacPos, NacOrient, NacVel, NacAcc, + RootPos, RootOrient, RootVel, RootAcc, + MeshPos_ar, MeshOrient_ar, MeshVel_ar, MeshAcc_ar) +except Exception as e: + print("{}".format(e)) + if DbgOuts == 1: + dbg_outfile.end() + #FIXME: temporary statement here + print("Exit after failed call to adi_calcOutput at T=0") + exit(1) + + +print(f"Time step: {i} at {time[i]}") +try: + adilib.adi_calcOutput(time[i], + outputChannelValues) +except Exception as e: + print("{}".format(e)) + if DbgOuts == 1: + dbg_outfile.end() + #FIXME: temporary statement here + print("Exit after failed call to adi_calcOutput at T=0") + exit(1) + +# get resulting forces +try: + adilib.adi_getrotorloads( + iturb, + MeshFrcMom) +except Exception as e: + print("{}".format(e)) + if DbgOuts == 1: + dbg_outfile.end() + #FIXME: temporary statement here + print("Exit after failed call to adi_getrotorloads at T=0") + exit(1) + + +## Write the debug output at t=t_initial +if DbgOuts == 1: + dbg_outfile.write(time[i],MeshPos_ar,MeshVel_ar,MeshAcc_ar,MeshFrcMom) +# Save the output at t=t_initial +allOutputChannelValues[i,:] = np.append(time[i],outputChannelValues) + + +# Timestep iteration +# Correction loop: +# 1. Set inputs at t+dt using either extrapolated values (or +# corrected values if in a correction step) from the structural +# solver +# 2. Call UpdateStates to propogate states from t -> t+dt +# 3. call Ifw_CalcOutput_C to get the resulting forces at t+dt using +# the updated state information for t+dt. These would be passed +# back to the structural solver at each step of the correction +# loop so that it can be used to tune the states of other modules +# (structural solver etc). +# End correction loop: +# 4. Once correction loop is complete, save the resulting values +# +# time[i-1] is at t +# time[i] is at t+dt +for i in range( 1, len(time)): + + # hard code to one turbine for now + iturb = 1 + + for correction in range(0, NumCorrections+1): + + #print(f"Correction step: {correction} for {time[i-1]} --> {time[i]}") + + # If there are correction steps, the inputs would be updated using outputs + # from the other modules. + # read position/motion from vtk + HubPos, HubOrient, HubVel, HubAcc = SetMotionHub(i) + NacPos, NacOrient, NacVel, NacAcc = SetMotionNac(i) + RootPos, RootOrient, RootVel, RootAcc = SetMotionRoot(i) + MeshPos_ar, MeshOrient_ar, MeshVel_ar, MeshAcc_ar, MeshFrcMom = SetMotionBlMesh(i) + + # Set motions for rotor + try: + adilib.adi_setrotormotion( + iturb, + HubPos, HubOrient, HubVel, HubAcc, + NacPos, NacOrient, NacVel, NacAcc, + RootPos, RootOrient, RootVel, RootAcc, + MeshPos_ar, MeshOrient_ar, MeshVel_ar, MeshAcc_ar) + except Exception as e: + print("{}".format(e)) + if DbgOuts == 1: + dbg_outfile.end() + #FIXME: temporary statement here + print("Exit after failed call to adi_setrotormotion at {time[i]}") + exit(1) + + + # Update the states from t to t+dt (only if not beyond end of sim) + try: + adilib.adi_updateStates(time[i-1], time[i]) + except Exception as e: + print("{}".format(e)) + if DbgOuts == 1: + dbg_outfile.end() + #FIXME: temporary statement here + print("Exit after failed call to adi_updateStates") + exit(1) + + # Calculate the outputs at t+dt + print(f"Time step: {i} at {time[i]}") + # NOTE: new input values may be available at this point from the + # structural solver, so update them here. + # read position/motion from vtk + HubPos, HubOrient, HubVel, HubAcc = SetMotionHub(i) + NacPos, NacOrient, NacVel, NacAcc = SetMotionNac(i) + RootPos, RootOrient, RootVel, RootAcc = SetMotionRoot(i) + MeshPos_ar, MeshOrient_ar, MeshVel_ar, MeshAcc_ar, MeshFrcMom = SetMotionBlMesh(i) + + # Set motions for rotor + try: + adilib.adi_setrotormotion( + iturb, + HubPos, HubOrient, HubVel, HubAcc, + NacPos, NacOrient, NacVel, NacAcc, + RootPos, RootOrient, RootVel, RootAcc, + MeshPos_ar, MeshOrient_ar, MeshVel_ar, MeshAcc_ar) + except Exception as e: + print("{}".format(e)) + if DbgOuts == 1: + dbg_outfile.end() + #FIXME: temporary statement here + print("Exit after failed call to adi_setrotormotion at {time[i]}") + exit(1) + + + try: + adilib.adi_calcOutput(time[i], outputChannelValues) + except Exception as e: + print("{}".format(e)) + if DbgOuts == 1: + dbg_outfile.end() + #FIXME: temporary statement here + print(f"Exit after failed call to adi_calcOutput at time {time[i]}") + exit(1) + + # get resulting forces + try: + adilib.adi_getrotorloads( + iturb, + MeshFrcMom) + except Exception as e: + print("{}".format(e)) + if DbgOuts == 1: + dbg_outfile.end() + #FIXME: temporary statement here + print("Exit after failed call to adi_getrotorloads at {time[i]}") + exit(1) + + +## Write the debug output at t=t_initial + + # When coupled to a different code, this is where the Force/Moment info + # would be passed to the aerodynamic solver. + # + # For this regression test example, we will write this to file (in + # principle this could be aggregated and written out once at the end of + # the regression simulation, but for simplicity we are writting one line + # at a time during the call). The regression test will have one row for + # each timestep + position array entry. + if DbgOuts == 1: + dbg_outfile.write(time[i],MeshPos_ar,MeshVel_ar,MeshAcc_ar,MeshFrcMom) + + + # Store the channel outputs -- these are requested from within the IfW input + # file OutList section. In OpenFAST, these are added to the output + # channel array for all modules and written to that output file. For this + # example we will write to file at the end of the simulation in a single + # shot. + allOutputChannelValues[i,:] = np.append(time[i],outputChannelValues) + + +if DbgOuts == 1: + dbg_outfile.end() # close the debug output file + +# if we got this far, things must have succeeded +print("Simulation completed sucessfully") + + +# adi_end: Only need to call aerodyn_inflow_end once. +# NOTE: in the event of an error during the above Init or CalcOutput calls, +# the IfW_End routine will be called during that error handling. +# This works for IfW, but may not be a desirable way to handle +# errors in other codes (we may still want to retrieve some info +# from memory before clearing out everything). +# NOTE: Error handling from the adi_end call may not be entirely +# necessary, but we may want to know if some memory was not released +# properly or a file not closed correctly. +try: + adilib.adi_end() +except Exception as e: + print("{}".format(e)) + #FIXME: temporary statement here + print("Exit after failed call to adi_end") + exit(1) + + +# Now write the ouput channels to a file +OutFile=adi.WriteOutChans(output_file,adilib.output_channel_names,adilib.output_channel_units) +OutFile.write(allOutputChannelValues) +OutFile.end() + + + +#print("HydroDyn successful.") +exit() + diff --git a/modules/aerodyn/py_ad_B1n2_OLAF/visread.py b/modules/aerodyn/py_ad_B1n2_OLAF/visread.py new file mode 100644 index 000000000..8d5d365f7 --- /dev/null +++ b/modules/aerodyn/py_ad_B1n2_OLAF/visread.py @@ -0,0 +1,97 @@ +import numpy as np +import vtk + +def visread_positions_ref(filename): + reader = vtk.vtkXMLPolyDataReader() + + reader.SetFileName(filename) + reader.Update() + + _arName = [] + _numArrays = reader.GetNumberOfPointArrays() + for i in range(_numArrays): + _arName.append(reader.GetPointArrayName(i)) + + position_ar = np.array( reader.GetOutput().GetPoints().GetData(), dtype="float32") + _orientX = np.array( reader.GetOutput().GetPointData().GetArray(_arName.index('RefOrientationX')),dtype="float64") + _orientY = np.array( reader.GetOutput().GetPointData().GetArray(_arName.index('RefOrientationY')),dtype="float64") + _orientZ = np.array( reader.GetOutput().GetPointData().GetArray(_arName.index('RefOrientationZ')),dtype="float64") + + orient_ar = np.hstack((_orientX, _orientY, _orientZ)) + + numpts_pos = np.size(position_ar,0) + numpts_ori = np.size(orient_ar,0) + + if numpts_pos != numpts_ori: + raise Exception("\nvisread_positions: Number of position and orientation points differ in file "+filename) + + return position_ar, orient_ar, numpts_pos + + +def visread_positions(filename): + reader = vtk.vtkXMLPolyDataReader() + + reader.SetFileName(filename) + reader.Update() + + _arName = [] + _numArrays = reader.GetNumberOfPointArrays() + for i in range(_numArrays): + _arName.append(reader.GetPointArrayName(i)) + + position_ar = np.array( reader.GetOutput().GetPoints().GetData(), dtype="float32") + _orientX = np.array( reader.GetOutput().GetPointData().GetArray(_arName.index('OrientationX')),dtype="float64") + _orientY = np.array( reader.GetOutput().GetPointData().GetArray(_arName.index('OrientationY')),dtype="float64") + _orientZ = np.array( reader.GetOutput().GetPointData().GetArray(_arName.index('OrientationZ')),dtype="float64") + + orient_ar = np.hstack((_orientX, _orientY, _orientZ)) + + numpts_pos = np.size(position_ar,0) + numpts_ori = np.size(orient_ar,0) + + if numpts_pos != numpts_ori: + raise Exception("\nvisread_positions: Number of position and orientation points differ in file "+filename) + + return position_ar, orient_ar, numpts_pos + + +def visread_velacc(filename,numpts): + reader = vtk.vtkXMLPolyDataReader() + + reader.SetFileName(filename) + reader.Update() + + _arName = [] + _numArrays = reader.GetNumberOfPointArrays() + for i in range(_numArrays): + _arName.append(reader.GetPointArrayName(i)) + + if 'TranslationalVelocity' in _arName: + _TV = np.array( reader.GetOutput().GetPointData().GetArray(_arName.index('TranslationalVelocity')),dtype="float32") + if np.size(_TV,0) != numpts: + raise Exception("\nvisread_velacc: Unexpected number of translational velocity points in file"+filename+" (expected "+str(numpts)+", got "+str(np.size(_TV,0))+")") + else: + _TV = np.zeros((numpts,3),dtype="float32") + if 'RotationalVelocity' in _arName: + _RV = np.array( reader.GetOutput().GetPointData().GetArray(_arName.index('RotationalVelocity' )),dtype="float32") + if np.size(_RV,0) != numpts: + raise Exception("\nvisread_velacc: Unexpected number of rotational velocity points in file"+filename+" (expected "+str(numpts)+", got "+str(np.size(_RV,0))+")") + else: + _RV = np.zeros((numpts,3),dtype="float32") + vel_ar = np.hstack((_TV, _RV)) + + if 'TranslationalAcceleration' in _arName: + _TA = np.array( reader.GetOutput().GetPointData().GetArray(_arName.index('TranslationalAcceleration')),dtype="float32") + if np.size(_TA,0) != numpts: + raise Exception("\nvisread_velacc: Unexpected number of translational acceleration points in file"+filename+" (expected "+str(numpts)+", got "+str(np.size(_TA,0))+")") + else: + _TA = np.zeros((numpts,3),dtype="float32") + if 'RotationalAcceleration' in _arName: + _RA = np.array( reader.GetOutput().GetPointData().GetArray(_arName.index('RotationalAcceleration' )),dtype="float32") + if np.size(_RA,0) != numpts: + raise Exception("\nvisread_velacc: Unexpected number of rotational acceleration points in file"+filename+" (expected "+str(numpts)+", got "+str(np.size(_RA,0))+")") + else: + _RA = np.zeros((numpts,3),dtype="float32") + acc_ar = np.hstack((_TA, _RA)) + + return vel_ar, acc_ar diff --git a/modules/aerodyn/py_ad_B1n2_OLAF/vtkRef/AD_BladeMotion1.000000000.vtp b/modules/aerodyn/py_ad_B1n2_OLAF/vtkRef/AD_BladeMotion1.000000000.vtp new file mode 100644 index 000000000..6834f0a24 --- /dev/null +++ b/modules/aerodyn/py_ad_B1n2_OLAF/vtkRef/AD_BladeMotion1.000000000.vtp @@ -0,0 +1,56 @@ 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