------- AERODYN for OpenFAST INPUT FILE -------------------------------------------------------------
Description line that will be printed in the output file and written to the screen.
======  General Options  ============================================================================
False         Echo               - Echo the input to "<rootname>.AD.ech"?  (flag)
"default"     DTAero             - Time interval for aerodynamic calculations {or "default"} (s)
          1   Wake_Mod           - Wake/induction model (switch) {0=none, 1=BEMT, 3=OLAF} [Wake_Mod cannot be 2 or 3 when linearizing]
          1   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         CavitCheck         - Perform cavitation check? (flag) [UA_Mod must be 0 when CavitCheck=true]
False         Buoyancy           - Include buoyancy effects? (flag)
False         NacelleDrag        - Include Nacelle Drag effects? (flag)
False         CompAA             - Flag to compute AeroAcoustics calculation [used only when Wake_Mod = 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 Wake_Mod=0 or 3, except for BEM_Mod]
          2   BEM_Mod            - BEM model {1=legacy NoSweepPitchTwist, 2=polar} (switch) [used for all Wake_Mod to determine output coordinate system]
--- Skew correction
          1   Skew_Mod           - Skew model {0=No skew model, -1=Remove non-normal component for linearization, 1=skew model active}
True          SkewMomCorr        - Turn the skew momentum correction on or off [used only when Skew_Mod=1]
          1   SkewRedistr_Mod    - Type of skewed-wake correction model (switch) {0=no redistribution, 1=Glauert/Pitt/Peters, default=1} [used only when Skew_Mod=1]
"default"     SkewRedistrFactor  - Constant used in Pitt/Peters skewed wake model {or "default" is 15/32*pi} (-) [used only when Skew_Mod=1 and SkewRedistr_Mod=1]
--- BEM algorithm 
True          TipLoss            - Use the Prandtl tip-loss model? (flag) [unused when Wake_Mod=0 or 3]
True          HubLoss            - Use the Prandtl hub-loss model? (flag) [unused when Wake_Mod=0 or 3]
True          TanInd             - Include tangential induction in BEMT calculations? (flag) [unused when Wake_Mod=0 or 3]
True          AIDrag             - Include the drag term in the axial-induction calculation? (flag) [unused when Wake_Mod=0 or 3]
True          TIDrag             - Include the drag term in the tangential-induction calculation? (flag) [unused when Wake_Mod=0,3 or TanInd=FALSE]
"Default"     IndToler           - Convergence tolerance for BEMT nonlinear solve residual equation {or "default"} (-) [unused when Wake_Mod=0 or 3]
        100   MaxIter            - Maximum number of iteration steps (-) [unused when Wake_Mod=0]
--- Shear correction 
False         SectAvg           - Use sector averaging (flag)
1             SectAvgWeighting  - Weighting function for sector average  {1=Uniform, default=1}  within a sector centered on the blade (switch) [used only when SectAvg=True] 
5             SectAvgNPoints    - Number of points per sectors (-) {default=5} [used only when SectAvg=True]
-60           SectAvgPsiBwd     - Backward azimuth relative to blade where the sector starts (<=0) {default=-60} (deg) [used only when SectAvg=True]
 60           SectAvgPsiFwd     - Forward azimuth relative to blade where the sector ends (>=0) {default=60} (deg) [used only when SectAvg=True]
--- Dynamic wake/inflow
          2   DBEMT_Mod          - Type of dynamic BEMT (DBEMT) model {0=No Dynamic Wake, -1=Frozen Wake for linearization, 1:constant tau1, 2=time-dependent tau1, 3=constant tau1 with continuous formulation} (-)
         20   tau1_const         - Time constant for DBEMT (s) [used only when DBEMT_Mod=1 or 3]
======  OLAF -- cOnvecting LAgrangian Filaments (Free Vortex Wake) Theory Options  ================== [used only when Wake_Mod=3]
"unused"      OLAFInputFileName  - Input file for OLAF [used only when Wake_Mod=3]
======  Unsteady Airfoil Aerodynamics Options  ====================================================
True          AoA34              - Sample the angle of attack (AoA) at the 3/4 chord or the AC point {default=True} [always used]
          3   UA_Mod             - Unsteady Aero Model Switch (switch) {0=Quasi-steady (no UA), 2=B-L Gonzalez, 3=B-L Minnema/Pierce, 4=B-L HGM 4-states, 5=B-L HGM+vortex 5 states, 6=Oye, 7=Boeing-Vertol}
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 UA_Mod=2 or UA_Mod=3]
          3   IntegrationMethod  - Switch to indicate which integration method UA uses (1=RK4, 2=AB4, 3=ABM4, 4=BDF2)
          0   UAStartRad         - Starting radius for dynamic stall (fraction of rotor radius [0.0,1.0]) [used only when UA_Mod>0; if line is missing UAStartRad=0]
          1   UAEndRad           - Ending radius for dynamic stall (fraction of rotor radius [0.0,1.0]) [used only when UA_Mod>0; if line is missing UAEndRad=1]
======  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 (-)
         10   NumAFfiles         - Number of airfoil files used (-)
"Airfoils/UAE_VI/cylinder.dat"    AFNames            - Airfoil file names (NumAFfiles lines) (quoted strings)
"Airfoils/UAE_VI/Mod_S809_129.dat"
"Airfoils/UAE_VI/Mod_S809_185.dat"
"Airfoils/UAE_VI/Mod_S809_242.dat"
"Airfoils/UAE_VI/Mod_S809_298.dat"
"Airfoils/UAE_VI/Mod_S809_354.dat"
"Airfoils/UAE_VI/Mod_S809_410.dat"
"Airfoils/UAE_VI/Mod_S809_600.dat"
"Airfoils/UAE_VI/Mod_S809_800.dat"
"Airfoils/UAE_VI/Mod_S809_Outboard.dat"
======  Rotor/Blade Properties  =====================================================================
True          UseBlCm            - Include aerodynamic pitching moment in calculations?  (flag)
"Test01_UAE_AeroDyn_blade.dat"    ADBlFile(1)        - Name of file containing distributed aerodynamic properties for Blade #1 (-)
"Test01_UAE_AeroDyn_blade.dat"    ADBlFile(2)        - Name of file containing distributed aerodynamic properties for Blade #2 (-) [unused if NumBl < 2]
"Test01_UAE_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   VolHub             - Hub volume (m^3)
          0   HubCenBx           - Hub center of buoyancy x direction offset (m)
======  Nacelle Properties ========================================================================== [used only when Buoyancy=True or NacelleDrag=True]
          0   VolNac             - Nacelle volume (m^3)
    0, 0, 0   NacCenB            - Position of nacelle center of buoyancy from yaw bearing in nacelle coordinates (m)
    0, 0, 0   NacArea            - Projected area of the nacelle in X, Y, Z in the nacelle coordinate system (m^2)
    0, 0, 0   NacCd              - Drag coefficient for the nacelle areas defined above (-)
    0, 0, 0   NacDragAC          - Position of aerodynamic center of nacelle drag 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]
          5   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 when TwrShadow=2; TwrCb used only when Buoyancy=True
(m)              (m)           (-)            (-)            (-)
0.0000000E+00  6.0000000E+00  0.0000000E+00  1.0000000E-01  0.0000000E+00  
2.0000000E+01  5.5000000E+00  0.0000000E+00  1.0000000E-01  0.0000000E+00  
4.0000000E+01  5.0000000E+00  0.0000000E+00  1.0000000E-01  0.0000000E+00  
6.0000000E+01  4.5000000E+00  0.0000000E+00  1.0000000E-01  0.0000000E+00  
8.0000000E+01  4.0000000E+00  0.0000000E+00  1.0000000E-01  0.0000000E+00  
======  Outputs  ====================================================================================
True          SumPrint            - Generate a summary file listing input options and interpolated properties to "<rootname>.AD.sum"? (flag)
          4   NBlOuts             - Number of blade node outputs [0 - 9] (-)
          1,          3,          4,          6    BlOutNd             - Blade nodes whose values will be output  (-)
          0   NTwOuts             - Number of tower node outputs [0 - 9]  (-)
          1   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, (-)
"B1N1VDisx, B1N1VDisy, B1N1VDisz" ! disturbed wind velocity at Blade 1, Node 1
"B1N2VDisx, B1N2VDisy, B1N2VDisz" ! disturbed wind velocity at Blade 1, Node 2
"B1N3VDisx, B1N3VDisy, B1N3VDisz" ! disturbed wind velocity at Blade 1, Node 3
"B1N1STVx,  B1N1STVy,  B1N1STVz"  ! structural translational velocity at Blade 1, Node 1
"B1N2STVx,  B1N2STVy,  B1N2STVz"  ! structural translational velocity at Blade 1, Node 2
"B1N3STVx,  B1N3STVy,  B1N3STVz"  ! structural translational velocity at Blade 1, Node 2
"RtSpeed, RtSkew, B1Azimuth"       
"B1N1AxInd, B1N2AxInd, B1N3AxInd"  
"B1N1Alpha, B1N2Alpha, B1N3Alpha"  
"B1N1Theta, B1N2Theta, B1N3Theta"  
END of OutList section (the word "END" must appear in the first 3 columns of the last OutList line)
====== Outputs for all blade stations (same ending as above for B1N1.... =========================== [optional section]
          1   BldNd_BladesOut     - Number of blades to output all node information at.  Up to number of blades on turbine. (-)
"All"         BldNd_BlOutNd       - Specify a portion of the nodes to output. {"ALL", "Tip", "Root", or a list of node numbers} (-)
              OutList_Nodal       - The next line(s) contains a list of output parameters.  See OutListParameters.xlsx for a listing of available output channels, (-)
"Fx, Fy"                   
"Vx, Vy"                   
"Vrel"                     
"TnInd"                    
"AxInd"                    
"Theta"                    
"Phi"                      
"Vindx"                    
"Vindy"                    
"Alpha"                    
END (the word "END" must appear in the first 3 columns of this last OutList line in the optional nodal output section)
====================================================================================================
