diff --git a/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/NRELOffshrBsline5MW_AeroDyn_blade.dat b/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/NRELOffshrBsline5MW_AeroDyn_blade.dat new file mode 100644 index 000000000..9d541024d --- /dev/null +++ b/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/NRELOffshrBsline5MW_AeroDyn_blade.dat @@ -0,0 +1,28 @@ +------- AERODYN v15.00.* BLADE DEFINITION INPUT FILE ------------------------------------- +NREL 5.0 MW offshore baseline aerodynamic blade input properties; note that we need to add the aerodynamic center to this file +====== Blade Properties ================================================================= + 19 NumBlNds - Number of blade nodes used in the analysis (-) + BlSpn BlCrvAC BlSwpAC BlCrvAng BlTwist BlChord BlAFID + (m) (m) (m) (deg) (deg) (m) (-) +0.0000000E+00 0.0000000E+00 0.0000000E+00 0.0000000E+00 1.3308000E+01 3.5420000E+00 1 +1.3667000E+00 -8.1531745E-04 -3.4468858E-03 0.0000000E+00 1.3308000E+01 3.5420000E+00 1 +4.1000000E+00 -2.4839790E-02 -1.0501421E-01 0.0000000E+00 1.3308000E+01 3.8540000E+00 1 +6.8333000E+00 -5.9469375E-02 -2.5141635E-01 0.0000000E+00 1.3308000E+01 4.1670000E+00 2 +1.0250000E+01 -1.0909141E-01 -4.6120149E-01 0.0000000E+00 1.3308000E+01 4.5570000E+00 3 +1.4350000E+01 -1.1573354E-01 -5.6986665E-01 0.0000000E+00 1.1480000E+01 4.6520000E+00 4 +1.8450000E+01 -9.8316709E-02 -5.4850833E-01 0.0000000E+00 1.0162000E+01 4.4580000E+00 4 +2.2550000E+01 -8.3186967E-02 -5.2457001E-01 0.0000000E+00 9.0110000E+00 4.2490000E+00 5 +2.6650000E+01 -6.7933232E-02 -4.9624675E-01 0.0000000E+00 7.7950000E+00 4.0070000E+00 6 +3.0750000E+01 -5.3393159E-02 -4.6544755E-01 0.0000000E+00 6.5440000E+00 3.7480000E+00 6 +3.4850000E+01 -4.0899260E-02 -4.3583519E-01 0.0000000E+00 5.3610000E+00 3.5020000E+00 7 +3.8950000E+01 -2.9722933E-02 -4.0591323E-01 0.0000000E+00 4.1880000E+00 3.2560000E+00 7 +4.3050000E+01 -2.0511081E-02 -3.7569051E-01 0.0000000E+00 3.1250000E+00 3.0100000E+00 8 +4.7150000E+01 -1.3980013E-02 -3.4521705E-01 0.0000000E+00 2.3190000E+00 2.7640000E+00 8 +5.1250000E+01 -8.3819737E-03 -3.1463837E-01 0.0000000E+00 1.5260000E+00 2.5180000E+00 8 +5.4666700E+01 -4.3546914E-03 -2.8909220E-01 0.0000000E+00 8.6300000E-01 2.3130000E+00 8 +5.7400000E+01 -1.6838383E-03 -2.6074456E-01 0.0000000E+00 3.7000000E-01 2.0860000E+00 8 +6.0133300E+01 -3.2815226E-04 -1.7737470E-01 0.0000000E+00 1.0600000E-01 1.4190000E+00 8 +6.1499900E+01 -3.2815226E-04 -1.7737470E-01 0.0000000E+00 1.0600000E-01 1.4190000E+00 8 + +!bjj: because of precision in the BD-AD coupling, 61.5m didn't work, so I changed it to 61.4999m +6.1500000E+01 -3.2815226E-04 -1.7737470E-01 0.0000000E+00 1.0600000E-01 1.4190000E+00 8 diff --git a/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/NRELOffshrBsline5MW_Blade.dat b/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/NRELOffshrBsline5MW_Blade.dat new file mode 100644 index 000000000..cf5aa25df --- /dev/null +++ b/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/NRELOffshrBsline5MW_Blade.dat @@ -0,0 +1,83 @@ +------- ELASTODYN V1.00.* INDIVIDUAL BLADE INPUT FILE -------------------------- +NREL 5.0 MW offshore baseline blade input properties. +---------------------- BLADE PARAMETERS ---------------------------------------- + 49 NBlInpSt - Number of blade input stations (-) + 0.477465 BldFlDmp(1) - Blade flap mode #1 structural damping in percent of critical (%) + 0.477465 BldFlDmp(2) - Blade flap mode #2 structural damping in percent of critical (%) + 0.477465 BldEdDmp(1) - Blade edge mode #1 structural damping in percent of critical (%) +---------------------- BLADE ADJUSTMENT FACTORS -------------------------------- + 1 FlStTunr(1) - Blade flapwise modal stiffness tuner, 1st mode (-) + 1 FlStTunr(2) - Blade flapwise modal stiffness tuner, 2nd mode (-) + 1.04536 AdjBlMs - Factor to adjust blade mass density (-) !bjj: value for AD14=1.04536; value for AD15=1.057344 (it would be nice to enter the requested blade mass instead of a factor here) + 1 AdjFlSt - Factor to adjust blade flap stiffness (-) + 1 AdjEdSt - Factor to adjust blade edge stiffness (-) +---------------------- DISTRIBUTED BLADE PROPERTIES ---------------------------- + BlFract PitchAxis StrcTwst BMassDen FlpStff EdgStff + (-) (-) (deg) (kg/m) (Nm^2) (Nm^2) +0.0000000E+00 2.5000000E-01 1.3308000E+01 6.7893500E+02 1.8110000E+10 1.8113600E+10 +3.2500000E-03 2.5000000E-01 1.3308000E+01 6.7893500E+02 1.8110000E+10 1.8113600E+10 +1.9510000E-02 2.5049000E-01 1.3308000E+01 7.7336300E+02 1.9424900E+10 1.9558600E+10 +3.5770000E-02 2.5490000E-01 1.3308000E+01 7.4055000E+02 1.7455900E+10 1.9497800E+10 +5.2030000E-02 2.6716000E-01 1.3308000E+01 7.4004200E+02 1.5287400E+10 1.9788800E+10 +6.8290000E-02 2.7941000E-01 1.3308000E+01 5.9249600E+02 1.0782400E+10 1.4858500E+10 +8.4550000E-02 2.9167000E-01 1.3308000E+01 4.5027500E+02 7.2297200E+09 1.0220600E+10 +1.0081000E-01 3.0392000E-01 1.3308000E+01 4.2405400E+02 6.3095400E+09 9.1447000E+09 +1.1707000E-01 3.1618000E-01 1.3308000E+01 4.0063800E+02 5.5283600E+09 8.0631600E+09 +1.3335000E-01 3.2844000E-01 1.3308000E+01 3.8206200E+02 4.9800600E+09 6.8844400E+09 +1.4959000E-01 3.4069000E-01 1.3308000E+01 3.9965500E+02 4.9368400E+09 7.0091800E+09 +1.6585000E-01 3.5294000E-01 1.3308000E+01 4.2632100E+02 4.6916600E+09 7.1676800E+09 +1.8211000E-01 3.6519000E-01 1.3181000E+01 4.1682000E+02 3.9494600E+09 7.2716600E+09 +1.9837000E-01 3.7500000E-01 1.2848000E+01 4.0618600E+02 3.3865200E+09 7.0817000E+09 +2.1465000E-01 3.7500000E-01 1.2192000E+01 3.8142000E+02 2.9337400E+09 6.2445300E+09 +2.3089000E-01 3.7500000E-01 1.1561000E+01 3.5282200E+02 2.5689600E+09 5.0489600E+09 +2.4715000E-01 3.7500000E-01 1.1072000E+01 3.4947700E+02 2.3886500E+09 4.9484900E+09 +2.6341000E-01 3.7500000E-01 1.0792000E+01 3.4653800E+02 2.2719900E+09 4.8080200E+09 +2.9595000E-01 3.7500000E-01 1.0232000E+01 3.3933300E+02 2.0500500E+09 4.5014000E+09 +3.2846000E-01 3.7500000E-01 9.6720000E+00 3.3000400E+02 1.8282500E+09 4.2440700E+09 +3.6098000E-01 3.7500000E-01 9.1100000E+00 3.2199000E+02 1.5887100E+09 3.9952800E+09 +3.9350000E-01 3.7500000E-01 8.5340000E+00 3.1382000E+02 1.3619300E+09 3.7507600E+09 +4.2602000E-01 3.7500000E-01 7.9320000E+00 2.9473400E+02 1.1023800E+09 3.4471400E+09 +4.5855000E-01 3.7500000E-01 7.3210000E+00 2.8712000E+02 8.7580000E+08 3.1390700E+09 +4.9106000E-01 3.7500000E-01 6.7110000E+00 2.6334300E+02 6.8130000E+08 2.7342400E+09 +5.2358000E-01 3.7500000E-01 6.1220000E+00 2.5320700E+02 5.3472000E+08 2.5548700E+09 +5.5610000E-01 3.7500000E-01 5.5460000E+00 2.4166600E+02 4.0890000E+08 2.3340300E+09 +5.8862000E-01 3.7500000E-01 4.9710000E+00 2.2063800E+02 3.1454000E+08 1.8287300E+09 +6.2115000E-01 3.7500000E-01 4.4010000E+00 2.0029300E+02 2.3863000E+08 1.5841000E+09 +6.5366000E-01 3.7500000E-01 3.8340000E+00 1.7940400E+02 1.7588000E+08 1.3233600E+09 +6.8618000E-01 3.7500000E-01 3.3320000E+00 1.6509400E+02 1.2601000E+08 1.1836800E+09 +7.1870000E-01 3.7500000E-01 2.8900000E+00 1.5441100E+02 1.0726000E+08 1.0201600E+09 +7.5122000E-01 3.7500000E-01 2.5030000E+00 1.3893500E+02 9.0880000E+07 7.9781000E+08 +7.8376000E-01 3.7500000E-01 2.1160000E+00 1.2955500E+02 7.6310000E+07 7.0961000E+08 +8.1626000E-01 3.7500000E-01 1.7300000E+00 1.0726400E+02 6.1050000E+07 5.1819000E+08 +8.4878000E-01 3.7500000E-01 1.3420000E+00 9.8776000E+01 4.9480000E+07 4.5487000E+08 +8.8130000E-01 3.7500000E-01 9.5400000E-01 9.0248000E+01 3.9360000E+07 3.9512000E+08 +8.9756000E-01 3.7500000E-01 7.6000000E-01 8.3001000E+01 3.4670000E+07 3.5372000E+08 +9.1382000E-01 3.7500000E-01 5.7400000E-01 7.2906000E+01 3.0410000E+07 3.0473000E+08 +9.3008000E-01 3.7500000E-01 4.0400000E-01 6.8772000E+01 2.6520000E+07 2.8142000E+08 +9.3821000E-01 3.7500000E-01 3.1900000E-01 6.6264000E+01 2.3840000E+07 2.6171000E+08 +9.4636000E-01 3.7500000E-01 2.5300000E-01 5.9340000E+01 1.9630000E+07 1.5881000E+08 +9.5447000E-01 3.7500000E-01 2.1600000E-01 5.5914000E+01 1.6000000E+07 1.3788000E+08 +9.6260000E-01 3.7500000E-01 1.7800000E-01 5.2484000E+01 1.2830000E+07 1.1879000E+08 +9.7073000E-01 3.7500000E-01 1.4000000E-01 4.9114000E+01 1.0080000E+07 1.0163000E+08 +9.7886000E-01 3.7500000E-01 1.0100000E-01 4.5818000E+01 7.5500000E+06 8.5070000E+07 +9.8699000E-01 3.7500000E-01 6.2000000E-02 4.1669000E+01 4.6000000E+06 6.4260000E+07 +9.9512000E-01 3.7500000E-01 2.3000000E-02 1.1453000E+01 2.5000000E+05 6.6100000E+06 +1.0000000E+00 3.7500000E-01 0.0000000E+00 1.0319000E+01 1.7000000E+05 5.0100000E+06 +---------------------- BLADE MODE SHAPES --------------------------------------- + 0.0622 BldFl1Sh(2) - Flap mode 1, coeff of x^2 + 1.7254 BldFl1Sh(3) - , coeff of x^3 + -3.2452 BldFl1Sh(4) - , coeff of x^4 + 4.7131 BldFl1Sh(5) - , coeff of x^5 + -2.2555 BldFl1Sh(6) - , coeff of x^6 + -0.5809 BldFl2Sh(2) - Flap mode 2, coeff of x^2 + 1.2067 BldFl2Sh(3) - , coeff of x^3 + -15.5349 BldFl2Sh(4) - , coeff of x^4 + 29.7347 BldFl2Sh(5) - , coeff of x^5 + -13.8255 BldFl2Sh(6) - , coeff of x^6 + 0.3627 BldEdgSh(2) - Edge mode 1, coeff of x^2 + 2.5337 BldEdgSh(3) - , coeff of x^3 + -3.5772 BldEdgSh(4) - , coeff of x^4 + 2.376 BldEdgSh(5) - , coeff of x^5 + -0.6952 BldEdgSh(6) - , coeff of x^6 + + diff --git a/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/README.md b/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/README.md new file mode 100644 index 000000000..17baf0ec7 --- /dev/null +++ b/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/README.md @@ -0,0 +1,18 @@ +Simple rigid motion test of 3 blade rotor through python interface with turbulent inflow +Based on 5MW\_OC4Semi\_WSt\_WavesWN regression test case + +- Rigid rotor, root node defined only +- Steady rotation speed +- Turbulent inflow + +NodePositions.txt -- order of points [x,y,z] + - hub point + - blade 1 -- 19 nodes + - blade 2 -- 19 nodes + - blade 3 -- 19 nodes + +NodeOrientations.txt -- order of points [r11,r12,r13,r21,r22,r23,r31,r32,r33] + - hub point + - blade 1 -- 19 nodes + - blade 2 -- 19 nodes + - blade 3 -- 19 nodes diff --git a/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/ad_primary.dat b/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/ad_primary.dat new file mode 100644 index 000000000..a34d3d54e --- /dev/null +++ b/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/ad_primary.dat @@ -0,0 +1,153 @@ +------- 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) + 1 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] + 1 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] + 2 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] + 4 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] +"unused" OLAFInputFileName - Input file for OLAF [used only when WakeMod=3] +====== Beddoes-Leishman Unsteady Airfoil Aerodynamics Options ===================================== [used only when AFAeroMod=2] + 3 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 ========================================================================= + 1 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 (-) + 8 NumAFfiles - Number of airfoil files used (-) +"../../../glue-codes/openfast/5MW_Baseline/Airfoils/Cylinder1.dat" AFNames - Airfoil file names (NumAFfiles lines) (quoted strings) +"../../../glue-codes/openfast/5MW_Baseline/Airfoils/Cylinder2.dat" +"../../../glue-codes/openfast/5MW_Baseline/Airfoils/DU40_A17.dat" +"../../../glue-codes/openfast/5MW_Baseline/Airfoils/DU35_A17.dat" +"../../../glue-codes/openfast/5MW_Baseline/Airfoils/DU30_A17.dat" +"../../../glue-codes/openfast/5MW_Baseline/Airfoils/DU25_A17.dat" +"../../../glue-codes/openfast/5MW_Baseline/Airfoils/DU21_A17.dat" +"../../../glue-codes/openfast/5MW_Baseline/Airfoils/NACA64_A17.dat" +====== Rotor/Blade Properties ===================================================================== +True UseBlCm - Include aerodynamic pitching moment in calculations? (flag) +"../../../glue-codes/openfast/5MW_Baseline/NRELOffshrBsline5MW_AeroDyn_blade.dat" ADBlFile(1) - Name of file containing distributed aerodynamic properties for Blade #1 (-) +"../../../glue-codes/openfast/5MW_Baseline/NRELOffshrBsline5MW_AeroDyn_blade.dat" ADBlFile(2) - Name of file containing distributed aerodynamic properties for Blade #2 (-) [unused if NumBl < 2] +"../../../glue-codes/openfast/5MW_Baseline/NRELOffshrBsline5MW_AeroDyn_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] + 11 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) (-) (-) (-) +1.0000000E+01 6.5000000E+00 1.0000000E+00 1.0000000E-01 0.0 +1.7760000E+01 6.2400000E+00 1.0000000E+00 1.0000000E-01 0.0 +2.5520000E+01 5.9700000E+00 1.0000000E+00 1.0000000E-01 0.0 +3.3280000E+01 5.7100000E+00 1.0000000E+00 1.0000000E-01 0.0 +4.1040000E+01 5.4500000E+00 1.0000000E+00 1.0000000E-01 0.0 +4.8800000E+01 5.1800000E+00 1.0000000E+00 1.0000000E-01 0.0 +5.6560000E+01 4.9200000E+00 1.0000000E+00 1.0000000E-01 0.0 +6.4320000E+01 4.6600000E+00 1.0000000E+00 1.0000000E-01 0.0 +7.2080000E+01 4.4000000E+00 1.0000000E+00 1.0000000E-01 0.0 +7.9840000E+01 4.1300000E+00 1.0000000E+00 1.0000000E-01 0.0 +8.7600000E+01 3.8700000E+00 1.0000000E+00 1.0000000E-01 0.0 +====== Outputs ==================================================================================== +True SumPrint - Generate a summary file listing input options and interpolated properties to ".AD.sum"? (flag) + 1 NBlOuts - Number of blade node outputs [0 - 9] (-) + 19 BlOutNd - Blade nodes whose values will be output (-) + 0 NTwOuts - Number of tower node outputs [0 - 9] (-) + 1, 2, 6 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, (-) +"RtFldCp" +"RtFldCt" +"RtFldCq" +"RtTSR" +END of input file (the word "END" must appear in the first 3 columns of this last OutList line) +---------------------- NODE OUTPUTS -------------------------------------------- + 3 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, FldDyn_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 +"VDisx" - x-component of disturbed wind velocity at each node +"VDisy" - y-component of disturbed wind velocity at each node +"VDisz" - z-component of disturbed 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 +"DynP" - Dynamic pressure at each node +"Re" - Reynolds number (in millions) at each node +"M" - Mach number at each node +"Vindx" - Axial induced wind velocity at each node +"Vindy" - Tangential induced wind velocity at each node +"AxInd" - Axial induction factor at each node +"TnInd" - Tangential induction factor at each node +"Alpha" - Angle of attack at each node +"Theta" - Pitch+Twist angle at each node +"Phi" - Inflow angle at each node +"Curve" - Curvature angle at each node +"Cl" - Lift force coefficient at each node +"Cd" - Drag force coefficient at each node +"Cm" - Pitching moment coefficient at each node +"Cx" - Normal force (to plane) coefficient at each node +"Cy" - Tangential force (to plane) coefficient at each node +"Cn" - Normal force (to chord) coefficient at each node +"Ct" - Tangential force (to chord) coefficient at each node +"Fl" - Lift force per unit length at each node +"Fd" - Drag force per unit length at each node +"Mm" - Pitching moment per unit length at each node +"Fx" - Normal force (to plane) per unit length at each node +"Fy" - Tangential force (to plane) per unit length 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 +"Clrnc" - Tower clearance at each node (based on the absolute distance to the nearest point in the tower from blade node B#N# minus the local tower radius, in the deflected configuration); please note that this clearance is only approximate because the calculation assumes that the blade is a line with no volume (however, the calculation does use the local tower radius); when blade node B#N# is above the tower top (or below the tower base), the absolute distance to the tower top (or base) minus the local tower radius, in the deflected configuration, is output +"Vx" - Local axial velocity +"Vy" - Local tangential velocity +"GeomPhi" - Geometric phi? If phi was solved using normal BEMT equations, GeomPhi = 1; otherwise, if it was solved geometrically, GeomPhi = 0. +"Chi" - Skew angle (used in skewed wake correction) -- not available for OLAF +"UA_Flag" - Flag indicating if UA is turned on for this node. -- not available for OLAF +"CpMin" - Pressure coefficient +"SgCav" - Cavitation number +"SigCr" - Critical cavitation number +"Gam" - Gamma -- circulation on blade +"Cl_Static" - Static portion of lift force coefficient at each node, without unsteady effects -- not available for BEMT/DBEMT +"Cd_Static" - Static portion of drag force coefficient at each node, without unsteady effects -- not available for BEMT/DBEMT +"Cm_Static" - Static portion of pitching moment coefficient at each node, without unsteady effects -- not available for BEMT/DBEMT +"Uin" - Axial induced velocity in rotating hub coordinates. Axial aligned with hub axis. rotor plane polar hub rotating coordinates +"Uit" - Tangential induced velocity in rotating hub coordinates. Tangential to the rotation plane. Perpendicular to blade aziumth. rotor plane polar hub rotating coordinates +"Uir" - Radial induced velocity in rotating hub coordinates. Radial outwards in rotation plane. Aligned with blade azimuth. rotor plane polar hub rotating coordinates +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_5MW_OC4Semi_WSt_WavesWN/ifw_primary.dat b/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/ifw_primary.dat new file mode 100644 index 000000000..e46a5ccf9 --- /dev/null +++ b/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/ifw_primary.dat @@ -0,0 +1,57 @@ +------- 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) + 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] ========================= + 8 HWindSpeed - Horizontal wind speed (m/s) + 90 RefHt - Reference height for horizontal wind speed (m) + 0 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) +====================== 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_5MW_OC4Semi_WSt_WavesWN/py_ad_driver.out b/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/py_ad_driver.out new file mode 100644 index 000000000..26c0e9a4a --- /dev/null +++ b/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/py_ad_driver.out @@ -0,0 +1,13 @@ +## This file was generated by AeroDyn_Inflow_Driver on Oct-24-2022 at 15:30:22 +## This file contains output channels requested from the OutList section of the AD15 and IfW input filespy_ad_driver.out +# +# +# +# + Time RtFldCp RtFldCt RtFldCq RtTSR AB1N001VUndx AB1N002VUndx AB1N003VUndx AB1N004VUndx AB1N005VUndx AB1N006VUndx AB1N007VUndx AB1N008VUndx AB1N009VUndx AB1N010VUndx AB1N011VUndx AB1N012VUndx AB1N013VUndx AB1N014VUndx AB1N015VUndx AB1N016VUndx AB1N017VUndx AB1N018VUndx AB1N019VUndx AB2N001VUndx AB2N002VUndx AB2N003VUndx AB2N004VUndx AB2N005VUndx AB2N006VUndx AB2N007VUndx AB2N008VUndx AB2N009VUndx AB2N010VUndx AB2N011VUndx AB2N012VUndx AB2N013VUndx AB2N014VUndx AB2N015VUndx AB2N016VUndx AB2N017VUndx AB2N018VUndx AB2N019VUndx AB3N001VUndx AB3N002VUndx AB3N003VUndx AB3N004VUndx AB3N005VUndx AB3N006VUndx AB3N007VUndx AB3N008VUndx AB3N009VUndx AB3N010VUndx AB3N011VUndx AB3N012VUndx AB3N013VUndx AB3N014VUndx AB3N015VUndx AB3N016VUndx AB3N017VUndx AB3N018VUndx AB3N019VUndx AB1N001VUndy AB1N002VUndy AB1N003VUndy AB1N004VUndy AB1N005VUndy AB1N006VUndy AB1N007VUndy AB1N008VUndy AB1N009VUndy AB1N010VUndy AB1N011VUndy AB1N012VUndy AB1N013VUndy AB1N014VUndy AB1N015VUndy AB1N016VUndy AB1N017VUndy AB1N018VUndy AB1N019VUndy AB2N001VUndy AB2N002VUndy AB2N003VUndy AB2N004VUndy AB2N005VUndy AB2N006VUndy AB2N007VUndy AB2N008VUndy AB2N009VUndy AB2N010VUndy AB2N011VUndy AB2N012VUndy AB2N013VUndy AB2N014VUndy AB2N015VUndy AB2N016VUndy AB2N017VUndy AB2N018VUndy AB2N019VUndy AB3N001VUndy AB3N002VUndy AB3N003VUndy AB3N004VUndy AB3N005VUndy AB3N006VUndy AB3N007VUndy AB3N008VUndy AB3N009VUndy AB3N010VUndy AB3N011VUndy AB3N012VUndy AB3N013VUndy AB3N014VUndy AB3N015VUndy AB3N016VUndy AB3N017VUndy AB3N018VUndy AB3N019VUndy AB1N001VUndz AB1N002VUndz AB1N003VUndz AB1N004VUndz AB1N005VUndz AB1N006VUndz AB1N007VUndz AB1N008VUndz AB1N009VUndz AB1N010VUndz AB1N011VUndz AB1N012VUndz AB1N013VUndz AB1N014VUndz AB1N015VUndz AB1N016VUndz AB1N017VUndz AB1N018VUndz AB1N019VUndz AB2N001VUndz AB2N002VUndz AB2N003VUndz AB2N004VUndz AB2N005VUndz AB2N006VUndz AB2N007VUndz AB2N008VUndz AB2N009VUndz AB2N010VUndz AB2N011VUndz AB2N012VUndz AB2N013VUndz AB2N014VUndz AB2N015VUndz AB2N016VUndz AB2N017VUndz AB2N018VUndz AB2N019VUndz AB3N001VUndz AB3N002VUndz AB3N003VUndz AB3N004VUndz AB3N005VUndz AB3N006VUndz AB3N007VUndz AB3N008VUndz AB3N009VUndz AB3N010VUndz AB3N011VUndz AB3N012VUndz AB3N013VUndz AB3N014VUndz AB3N015VUndz AB3N016VUndz AB3N017VUndz AB3N018VUndz AB3N019VUndz AB1N001VDisx AB1N002VDisx AB1N003VDisx AB1N004VDisx AB1N005VDisx AB1N006VDisx AB1N007VDisx AB1N008VDisx AB1N009VDisx AB1N010VDisx AB1N011VDisx AB1N012VDisx AB1N013VDisx AB1N014VDisx AB1N015VDisx AB1N016VDisx AB1N017VDisx AB1N018VDisx AB1N019VDisx AB2N001VDisx AB2N002VDisx AB2N003VDisx AB2N004VDisx AB2N005VDisx AB2N006VDisx AB2N007VDisx AB2N008VDisx AB2N009VDisx AB2N010VDisx AB2N011VDisx AB2N012VDisx AB2N013VDisx AB2N014VDisx AB2N015VDisx AB2N016VDisx AB2N017VDisx AB2N018VDisx AB2N019VDisx AB3N001VDisx AB3N002VDisx AB3N003VDisx AB3N004VDisx AB3N005VDisx AB3N006VDisx AB3N007VDisx AB3N008VDisx AB3N009VDisx AB3N010VDisx AB3N011VDisx AB3N012VDisx AB3N013VDisx AB3N014VDisx AB3N015VDisx AB3N016VDisx AB3N017VDisx AB3N018VDisx AB3N019VDisx AB1N001VDisy AB1N002VDisy AB1N003VDisy AB1N004VDisy AB1N005VDisy AB1N006VDisy AB1N007VDisy AB1N008VDisy AB1N009VDisy AB1N010VDisy AB1N011VDisy AB1N012VDisy AB1N013VDisy AB1N014VDisy AB1N015VDisy AB1N016VDisy AB1N017VDisy AB1N018VDisy AB1N019VDisy AB2N001VDisy AB2N002VDisy AB2N003VDisy AB2N004VDisy AB2N005VDisy AB2N006VDisy AB2N007VDisy AB2N008VDisy AB2N009VDisy AB2N010VDisy AB2N011VDisy AB2N012VDisy AB2N013VDisy AB2N014VDisy AB2N015VDisy AB2N016VDisy AB2N017VDisy AB2N018VDisy AB2N019VDisy AB3N001VDisy AB3N002VDisy AB3N003VDisy AB3N004VDisy AB3N005VDisy AB3N006VDisy AB3N007VDisy AB3N008VDisy AB3N009VDisy AB3N010VDisy AB3N011VDisy AB3N012VDisy AB3N013VDisy AB3N014VDisy AB3N015VDisy AB3N016VDisy AB3N017VDisy AB3N018VDisy AB3N019VDisy AB1N001VDisz AB1N002VDisz AB1N003VDisz AB1N004VDisz AB1N005VDisz AB1N006VDisz AB1N007VDisz AB1N008VDisz AB1N009VDisz AB1N010VDisz AB1N011VDisz AB1N012VDisz AB1N013VDisz AB1N014VDisz AB1N015VDisz AB1N016VDisz AB1N017VDisz AB1N018VDisz AB1N019VDisz AB2N001VDisz AB2N002VDisz AB2N003VDisz AB2N004VDisz AB2N005VDisz AB2N006VDisz AB2N007VDisz AB2N008VDisz AB2N009VDisz AB2N010VDisz AB2N011VDisz AB2N012VDisz AB2N013VDisz AB2N014VDisz AB2N015VDisz AB2N016VDisz AB2N017VDisz AB2N018VDisz AB2N019VDisz AB3N001VDisz AB3N002VDisz AB3N003VDisz AB3N004VDisz AB3N005VDisz AB3N006VDisz AB3N007VDisz AB3N008VDisz AB3N009VDisz AB3N010VDisz AB3N011VDisz AB3N012VDisz AB3N013VDisz AB3N014VDisz AB3N015VDisz AB3N016VDisz AB3N017VDisz AB3N018VDisz AB3N019VDisz AB1N001STVx AB1N002STVx AB1N003STVx AB1N004STVx AB1N005STVx AB1N006STVx AB1N007STVx AB1N008STVx AB1N009STVx AB1N010STVx AB1N011STVx AB1N012STVx AB1N013STVx AB1N014STVx AB1N015STVx AB1N016STVx AB1N017STVx AB1N018STVx AB1N019STVx AB2N001STVx AB2N002STVx AB2N003STVx AB2N004STVx AB2N005STVx AB2N006STVx AB2N007STVx AB2N008STVx AB2N009STVx AB2N010STVx AB2N011STVx AB2N012STVx AB2N013STVx AB2N014STVx AB2N015STVx AB2N016STVx AB2N017STVx AB2N018STVx AB2N019STVx AB3N001STVx AB3N002STVx AB3N003STVx AB3N004STVx AB3N005STVx AB3N006STVx AB3N007STVx AB3N008STVx AB3N009STVx 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AB1N017STVz AB1N018STVz AB1N019STVz AB2N001STVz AB2N002STVz AB2N003STVz AB2N004STVz AB2N005STVz AB2N006STVz AB2N007STVz AB2N008STVz AB2N009STVz AB2N010STVz AB2N011STVz AB2N012STVz AB2N013STVz AB2N014STVz AB2N015STVz AB2N016STVz AB2N017STVz AB2N018STVz AB2N019STVz AB3N001STVz AB3N002STVz AB3N003STVz AB3N004STVz AB3N005STVz AB3N006STVz AB3N007STVz AB3N008STVz AB3N009STVz AB3N010STVz AB3N011STVz AB3N012STVz AB3N013STVz AB3N014STVz AB3N015STVz AB3N016STVz AB3N017STVz AB3N018STVz AB3N019STVz AB1N001VRel AB1N002VRel AB1N003VRel AB1N004VRel AB1N005VRel AB1N006VRel AB1N007VRel AB1N008VRel AB1N009VRel AB1N010VRel AB1N011VRel AB1N012VRel AB1N013VRel AB1N014VRel AB1N015VRel AB1N016VRel AB1N017VRel AB1N018VRel AB1N019VRel AB2N001VRel AB2N002VRel AB2N003VRel AB2N004VRel AB2N005VRel AB2N006VRel AB2N007VRel AB2N008VRel AB2N009VRel AB2N010VRel AB2N011VRel AB2N012VRel AB2N013VRel AB2N014VRel AB2N015VRel AB2N016VRel AB2N017VRel AB2N018VRel AB2N019VRel AB3N001VRel AB3N002VRel AB3N003VRel AB3N004VRel 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AB2N001Uin AB2N002Uin AB2N003Uin AB2N004Uin AB2N005Uin AB2N006Uin AB2N007Uin AB2N008Uin AB2N009Uin AB2N010Uin AB2N011Uin AB2N012Uin AB2N013Uin AB2N014Uin AB2N015Uin AB2N016Uin AB2N017Uin AB2N018Uin AB2N019Uin AB3N001Uin AB3N002Uin AB3N003Uin AB3N004Uin AB3N005Uin AB3N006Uin AB3N007Uin AB3N008Uin AB3N009Uin AB3N010Uin AB3N011Uin AB3N012Uin AB3N013Uin AB3N014Uin AB3N015Uin AB3N016Uin AB3N017Uin AB3N018Uin AB3N019Uin AB1N001Uit AB1N002Uit AB1N003Uit AB1N004Uit AB1N005Uit AB1N006Uit AB1N007Uit AB1N008Uit AB1N009Uit AB1N010Uit AB1N011Uit AB1N012Uit AB1N013Uit AB1N014Uit AB1N015Uit AB1N016Uit AB1N017Uit AB1N018Uit AB1N019Uit AB2N001Uit AB2N002Uit AB2N003Uit AB2N004Uit AB2N005Uit AB2N006Uit AB2N007Uit AB2N008Uit AB2N009Uit AB2N010Uit AB2N011Uit AB2N012Uit AB2N013Uit AB2N014Uit AB2N015Uit AB2N016Uit AB2N017Uit AB2N018Uit AB2N019Uit AB3N001Uit AB3N002Uit AB3N003Uit AB3N004Uit AB3N005Uit AB3N006Uit AB3N007Uit AB3N008Uit AB3N009Uit AB3N010Uit AB3N011Uit AB3N012Uit AB3N013Uit AB3N014Uit AB3N015Uit AB3N016Uit AB3N017Uit AB3N018Uit AB3N019Uit AB1N001Uir AB1N002Uir AB1N003Uir AB1N004Uir AB1N005Uir AB1N006Uir AB1N007Uir AB1N008Uir AB1N009Uir AB1N010Uir AB1N011Uir AB1N012Uir AB1N013Uir AB1N014Uir AB1N015Uir AB1N016Uir AB1N017Uir AB1N018Uir AB1N019Uir AB2N001Uir AB2N002Uir AB2N003Uir AB2N004Uir AB2N005Uir AB2N006Uir AB2N007Uir AB2N008Uir AB2N009Uir AB2N010Uir AB2N011Uir AB2N012Uir AB2N013Uir AB2N014Uir AB2N015Uir AB2N016Uir AB2N017Uir AB2N018Uir AB2N019Uir AB3N001Uir AB3N002Uir AB3N003Uir AB3N004Uir AB3N005Uir AB3N006Uir AB3N007Uir AB3N008Uir AB3N009Uir AB3N010Uir AB3N011Uir AB3N012Uir AB3N013Uir AB3N014Uir AB3N015Uir AB3N016Uir AB3N017Uir AB3N018Uir AB3N019Uir 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) (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) (m/s) (m/s) (m/s) (m/s) (m/s) (m/s) (m/s) (m/s) (m/s) (m/s) 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(the "License"); +# you may not use this file except in compliance with the License. +# You may obtain a copy of the License at +# +# 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 +# +#FIXME: +# 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 +# set initial position, velocity, acceleration values +# call aerodyn_inflow_init once to initialize IfW +# Handle any resulting errors +# 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 +# 4. End +# call aerodyn_inflow_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 +sys.path.insert(0, os.path.sep.join(["..", "..", "..", "..", "..", "modules", "aerodyn", "python-lib"])) +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" +if sys.platform == "linux" or sys.platform == "linux2": + library_path = os.path.sep.join(["..", "..", "..", "..", "..", "build", "modules", "aerodyn", basename + ".so"]) +elif sys.platform == "darwin": + library_path = os.path.sep.join(["..", "..", "..", "..", "..", "build", "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(["..", "..", "..", "..", "..", "build", "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(["..", "..", "..", "..", "..", "build", "bin", "AeroDyn_Inflow_c_lib_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(["..", "..", "..", "..", "..", "build", "bin", "AeroDyn_Inflow_c_lib_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_primary.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=3 +vtkFieldLen=5 +TimeStepsToRun=4 +hubMeshRootName="5MW_OC4Semi_WSt_WavesWN.AD_HubMotion" +nacMeshRootName="5MW_OC4Semi_WSt_WavesWN.ED_Nacelle" +bldRootMeshRootName="5MW_OC4Semi_WSt_WavesWN.AD_BladeRootMotion" +bldMeshRootName="5MW_OC4Semi_WSt_WavesWN.ED_BladeLn2Mesh_motion" # 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() + + +#=============================================================================== +# 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.t_start = 0 # initial time +adilib.dt = 0.0125 # time interval that it's being called at +final_time = 60 # 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] + +# 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(adilib.t_start,(TimeStepsToRun+1)*adilib.dt,adilib.dt) # total time + increment because python doesnt include endpoint! + +# set some flags +adilib.storeHHvel = False +adilib.WrVTK = 2 # animation +adilib.WrVTK_Type = 3 # surface and line meshes +adilib.transposeDCM = 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). + +# 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 + +# 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 + +# AeroDyn_Inflow_Init: Only need to call aerodyn_inflow_init once +try: + adilib.aerodyn_inflow_init(adiAD_input_string_array,adiIfW_input_string_array) +except Exception as e: + print("{}".format(e)) # Exceptions handled in aerodyn_inflow_library.py + #FIXME: temporary statement here + print("Exit after failed call to aerodyn_inflow_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) + +print(f"Time step: {i} at {time[i]}") +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) +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") + 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)): + + 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) + + + # 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) + 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") + 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) + + 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) + 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]}") + exit(1) + + + # 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 + + +# aerodyn_inflow_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 +# 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() +except Exception as e: + print("{}".format(e)) + #FIXME: temporary statement here + print("Exit after failed call to aerodyn_inflow_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_5MW_OC4Semi_WSt_WavesWN/visread.py b/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/visread.py new file mode 100644 index 000000000..8d5d365f7 --- /dev/null +++ b/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/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_5MW_OC4Semi_WSt_WavesWN/vtkRef/5MW_OC4Semi_WSt_WavesWN.AD_BladeRootMotion1.00000.vtp b/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/vtkRef/5MW_OC4Semi_WSt_WavesWN.AD_BladeRootMotion1.00000.vtp new file mode 100644 index 000000000..172ccddb3 --- /dev/null +++ b/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/vtkRef/5MW_OC4Semi_WSt_WavesWN.AD_BladeRootMotion1.00000.vtp @@ -0,0 +1,36 @@ + + + + + + + 3.10068 0.00000 91.61185 + + + + + 0.00000 -1.41237 0.00000 + + + 0.93565 -0.00000 -0.11321 + + + -0.09341 -0.01365 -1.60564 + + + 0.03947 -0.06181 -0.01507 + + + 0.99705 0.00000 -0.07671 + + + -0.00000 1.00000 -0.00000 + + + 0.07671 0.00000 0.99705 + + + + + diff --git a/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/vtkRef/5MW_OC4Semi_WSt_WavesWN.AD_BladeRootMotion1.00001.vtp b/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/vtkRef/5MW_OC4Semi_WSt_WavesWN.AD_BladeRootMotion1.00001.vtp new file mode 100644 index 000000000..b3355d49a --- /dev/null +++ b/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/vtkRef/5MW_OC4Semi_WSt_WavesWN.AD_BladeRootMotion1.00001.vtp @@ -0,0 +1,36 @@ + + + + + + + 3.10067 -0.01766 91.61173 + + + + + -0.00111 -1.41247 -0.02000 + + + 0.93608 -0.00076 -0.11339 + + + -0.07992 -0.01449 -1.58931 + + + 0.03099 -0.05816 -0.01094 + + + 0.99705 -0.00051 -0.07671 + + + 0.00142 0.99993 0.01170 + + + 0.07669 -0.01177 0.99699 + + + + + diff --git a/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/vtkRef/5MW_OC4Semi_WSt_WavesWN.AD_BladeRootMotion1.00002.vtp b/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/vtkRef/5MW_OC4Semi_WSt_WavesWN.AD_BladeRootMotion1.00002.vtp new file mode 100644 index 000000000..406f34193 --- /dev/null +++ b/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/vtkRef/5MW_OC4Semi_WSt_WavesWN.AD_BladeRootMotion1.00002.vtp @@ -0,0 +1,36 @@ + + + + + + + 3.10065 -0.03531 91.61136 + + + + + -0.00190 -1.41268 -0.03960 + + + 0.93638 -0.00143 -0.11349 + + + -0.04551 -0.00079 -1.54326 + + + 0.00561 -0.04859 -0.00429 + + + 0.99705 -0.00103 -0.07670 + + + 0.00283 0.99972 0.02340 + + + 0.07666 -0.02355 0.99678 + + + + + diff --git a/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/vtkRef/5MW_OC4Semi_WSt_WavesWN.AD_BladeRootMotion1.00003.vtp b/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/vtkRef/5MW_OC4Semi_WSt_WavesWN.AD_BladeRootMotion1.00003.vtp new file mode 100644 index 000000000..75d972d1e --- /dev/null +++ b/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/vtkRef/5MW_OC4Semi_WSt_WavesWN.AD_BladeRootMotion1.00003.vtp @@ -0,0 +1,36 @@ + + + + + + + 3.10063 -0.05297 91.61074 + + + + + -0.00216 -1.41253 -0.05846 + + + 0.93622 -0.00195 -0.11349 + + + 0.01024 0.00964 -1.46960 + + + -0.02478 -0.03379 0.00416 + + + 0.99705 -0.00155 -0.07669 + + + 0.00425 0.99937 0.03510 + + + 0.07659 -0.03532 0.99644 + + + + + diff --git a/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/vtkRef/5MW_OC4Semi_WSt_WavesWN.AD_BladeRootMotion1.00004.vtp b/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/vtkRef/5MW_OC4Semi_WSt_WavesWN.AD_BladeRootMotion1.00004.vtp new file mode 100644 index 000000000..873d7f501 --- /dev/null +++ b/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/vtkRef/5MW_OC4Semi_WSt_WavesWN.AD_BladeRootMotion1.00004.vtp @@ -0,0 +1,36 @@ + + + + + + + 3.10060 -0.07063 91.60990 + + + + + -0.00160 -1.41237 -0.07627 + + + 0.93571 -0.00226 -0.11338 + + + 0.08079 0.02544 -1.37547 + + + -0.05920 -0.01518 0.01302 + + + 0.99705 -0.00206 -0.07669 + + + 0.00567 0.99889 0.04679 + + + 0.07651 -0.04709 0.99596 + + + + + diff --git a/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/vtkRef/5MW_OC4Semi_WSt_WavesWN.AD_BladeRootMotion1.00005.vtp b/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/vtkRef/5MW_OC4Semi_WSt_WavesWN.AD_BladeRootMotion1.00005.vtp new file mode 100644 index 000000000..4b1464f00 --- /dev/null +++ b/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/vtkRef/5MW_OC4Semi_WSt_WavesWN.AD_BladeRootMotion1.00005.vtp @@ -0,0 +1,36 @@ + + + + + + + 3.10059 -0.08828 91.60884 + + + + + -0.00009 -1.41193 -0.09280 + + + 0.93475 -0.00232 -0.11316 + + + 0.16106 0.04840 -1.26873 + + + -0.09371 0.00555 0.02105 + + + 0.99705 -0.00258 -0.07669 + + + 0.00708 0.99826 0.05846 + + + 0.07640 -0.05883 0.99534 + + + + + diff --git a/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/vtkRef/5MW_OC4Semi_WSt_WavesWN.AD_BladeRootMotion1_Reference.vtp b/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/vtkRef/5MW_OC4Semi_WSt_WavesWN.AD_BladeRootMotion1_Reference.vtp new file mode 100644 index 000000000..0a6d34c15 --- /dev/null +++ b/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/vtkRef/5MW_OC4Semi_WSt_WavesWN.AD_BladeRootMotion1_Reference.vtp @@ -0,0 +1,24 @@ + + + + + + + -4.93457 0.00000 91.49858 + + + + + 0.99905 0.00000 -0.04362 + + + -0.00000 1.00000 -0.00000 + + + 0.04362 0.00000 0.99905 + + + + + diff --git a/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/vtkRef/5MW_OC4Semi_WSt_WavesWN.AD_BladeRootMotion2.00000.vtp b/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/vtkRef/5MW_OC4Semi_WSt_WavesWN.AD_BladeRootMotion2.00000.vtp new file mode 100644 index 000000000..2a5170600 --- /dev/null +++ b/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/vtkRef/5MW_OC4Semi_WSt_WavesWN.AD_BladeRootMotion2.00000.vtp @@ -0,0 +1,36 @@ + + + + + + + 2.83066 -1.29780 89.38027 + + + + + -0.14693 0.70619 -1.21429 + + + 0.93565 -0.00000 -0.11321 + + + 0.26482 1.23129 0.30868 + + + 0.03947 -0.06181 -0.01507 + + + 0.98919 -0.03778 -0.14166 + + + 0.10403 -0.50000 0.85975 + + + -0.10331 -0.86520 -0.49067 + + + + + diff --git a/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/vtkRef/5MW_OC4Semi_WSt_WavesWN.AD_BladeRootMotion2.00001.vtp b/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/vtkRef/5MW_OC4Semi_WSt_WavesWN.AD_BladeRootMotion2.00001.vtp new file mode 100644 index 000000000..eadaa8cfc --- /dev/null +++ b/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/vtkRef/5MW_OC4Semi_WSt_WavesWN.AD_BladeRootMotion2.00001.vtp @@ -0,0 +1,36 @@ + + + + + + + 2.82884 -1.28888 89.36512 + + + + + -0.14355 0.72136 -1.21018 + + + 0.93608 -0.00076 -0.11339 + + + 0.27968 1.18836 0.35283 + + + 0.03099 -0.05816 -0.01094 + + + 0.98914 -0.03752 -0.14210 + + + 0.10331 -0.51017 0.85385 + + + -0.10453 -0.85925 -0.50075 + + + + + diff --git a/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/vtkRef/5MW_OC4Semi_WSt_WavesWN.AD_BladeRootMotion2.00002.vtp b/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/vtkRef/5MW_OC4Semi_WSt_WavesWN.AD_BladeRootMotion2.00002.vtp new file mode 100644 index 000000000..307f0a266 --- /dev/null +++ b/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/vtkRef/5MW_OC4Semi_WSt_WavesWN.AD_BladeRootMotion2.00002.vtp @@ -0,0 +1,36 @@ + + + + + + + 2.82707 -1.27977 89.35002 + + + + + -0.13990 0.73583 -1.20528 + + + 0.93638 -0.00143 -0.11349 + + + 0.30452 1.12024 0.44808 + + + 0.00561 -0.04859 -0.00429 + + + 0.98909 -0.03725 -0.14252 + + + 0.10257 -0.52027 0.84782 + + + -0.10573 -0.85319 -0.51078 + + + + + diff --git a/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/vtkRef/5MW_OC4Semi_WSt_WavesWN.AD_BladeRootMotion2.00003.vtp b/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/vtkRef/5MW_OC4Semi_WSt_WavesWN.AD_BladeRootMotion2.00003.vtp new file mode 100644 index 000000000..3aa942641 --- /dev/null +++ b/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/vtkRef/5MW_OC4Semi_WSt_WavesWN.AD_BladeRootMotion2.00003.vtp @@ -0,0 +1,36 @@ + + + + + + + 2.82535 -1.27049 89.33499 + + + + + -0.13590 0.74930 -1.19886 + + + 0.93622 -0.00195 -0.11349 + + + 0.33975 1.03494 0.57495 + + + -0.02478 -0.03379 0.00416 + + + 0.98904 -0.03699 -0.14294 + + + 0.10181 -0.53031 0.84167 + + + -0.10693 -0.84700 -0.52073 + + + + + diff --git a/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/vtkRef/5MW_OC4Semi_WSt_WavesWN.AD_BladeRootMotion2.00004.vtp b/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/vtkRef/5MW_OC4Semi_WSt_WavesWN.AD_BladeRootMotion2.00004.vtp new file mode 100644 index 000000000..8c07c3ae1 --- /dev/null +++ b/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/vtkRef/5MW_OC4Semi_WSt_WavesWN.AD_BladeRootMotion2.00004.vtp @@ -0,0 +1,36 @@ + + + + + + + 2.82367 -1.26104 89.32006 + + + + + -0.13140 0.76166 -1.19078 + + + 0.93571 -0.00226 -0.11338 + + + 0.38005 0.94386 0.72477 + + + -0.05920 -0.01518 0.01302 + + + 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