SumPrint error with OpenFAST 3.0

Hi I have a Aerodyn file that gives a “SumPrint” error.
I tried with ECHO - TRUE and the .ech stops at

Tower Influence and Aerodynamics 

That part of Aerodyn.dat file is:

======  Rotor Properties  ===========================================================================
TRUE                             UseBlCm - Include aerodynamic pitching moment in calculations? (flag)
"Blade.dat"                  ADBlFile(1) - Name of file containing distributed aerodynamic properties for Blade #1 (file path)
"Blade.dat"                  ADBlFile(2) - Name of file containing distributed aerodynamic properties for Blade #2 (file path)
"Blade.dat"                  ADBlFile(3) - Name of file containing distributed aerodynamic properties for Blade #3 [unused if NumBl < 3] (file path)
======  Tower Influence and Aerodynamics ============================================================= [used only when TwrPotent/=0, TwrShadow=True, or TwrAero=True]
                  11           NumTwrNds  - Number of tower nodes used in the analysis[used only when TwrInflnc/=0, or TwrAero=True] (-)
             TwrElev             TwrDiam               TwrCd               TwrTI
                 (m)                 (m)                 (-)                 (-)
       1.0000000E+01       6.5000000E+00       1.0000000E+00       1.0000000E-01
       1.7760000E+01       6.2400000E+00       1.0000000E+00       1.0000000E-01
       2.5520000E+01       5.9700000E+00       1.0000000E+00       1.0000000E-01
       3.3280000E+01       5.7100000E+00       1.0000000E+00       1.0000000E-01
       4.1040000E+01       5.4500000E+00       1.0000000E+00       1.0000000E-01
       4.8800000E+01       5.1800000E+00       1.0000000E+00       1.0000000E-01
       5.6560000E+01       4.9200000E+00       1.0000000E+00       1.0000000E-01
       6.4320000E+01       4.6600000E+00       1.0000000E+00       1.0000000E-01
       7.2080000E+01       4.4000000E+00       1.0000000E+00       1.0000000E-01
       7.9840000E+01       4.1300000E+00       1.0000000E+00       1.0000000E-01
       8.7600000E+01       3.8700000E+00       1.0000000E+00       1.0000000E-01
======  Outputs  ====================================================================================
FALSE                           SumPrint - Generate a summary file listing input options and interpolated properties to "<rootname>.AD.sum"? (flag)
                   8             NBlOuts - Number of blade node outputs [0 - 9] (-)
1, 2, 3, 4, 5, 6, 7, 8             BlOutNd - Blade nodes whose values will be output (-)
                   9             NTwOuts - Number of tower node outputs [0 - 9] (-)
3, 4, 5, 6, 7, 8, 9, 10, 11             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, (-)

It’s running with V2.6.
Can you please point out the error in this w.r.t V3.0

Dear @Ashok.Jammi,

I’m not aware of changes made to the AeroDyn input file between v2.6 and v3.0 of OpenFAST, but can you share your complete AeroDyn input file and Echo file?

Best regards,

Hi @Jason.Jonkman ,

AeroDyn file:

------- AERODYN v15.02.* INPUT FILE -----------------------------------------------------------------
OC4 3.1 Modified (control system test)
======  General Options  ============================================================================
TRUE                               Echo - Echo input to "<rootname>.AD.ech"? (flag)
"DEFAULT"                         DTAero - Time interval for aerodynamic calculations {or "default"} (s)
                   1             WakeMod - Type of wake/induction model (switch)
                   2           AFAeroMod - Type of blade aerofoil aerodynamics model (switch)
                   1           TwrPotent - Type tower influence on wind based on potential flow around the tower (switch)
                   0           TwrShadow - Calculate tower influence on wind based on downstream tower shadow? (switch)
TRUE                             TwrAero - Calculate tower aerodynamic loads? (flag)
FALSE                         FrozenWake - Assume frozen wake during linearization? (flag)
FALSE                         CavitCheck - Perform cavitation check? (flag)
FALSE                             CompAA - Flag to compute AeroAcoustics calculation (flag)
"UNUSED"                    AA_InputFile - AeroAcoustics input file (file path)
======  Environmental Conditions  ===================================================================
               1.225             AirDens - Air density (kg/m^3)
           1.464E-05             KinVisc - Kinematic air viscosity (m^2/s)
                 335            SpdSound - Speed of sound (m/s)
              103500                Patm - Atmospheric pressure (Pa)
                1700                Pvap - Vapour pressure of fluid (Pa)
                 0.5          FluidDepth - Water depth above mid-hub height (m)
======  Blade-Element/Momentum Theory Options  ====================================================== [used only when WakeMod=1]
                   2             SkewMod - Type of skewed-wake correction model (switch)
"DEFAULT"                  SkewModFactor - Constant used in Pitt/Peters skewed wake model {or "default" is 15/32*pi} (-)
TRUE                             TipLoss - Use the Prandtl tip-loss model? (flag)
TRUE                             HubLoss - Use the Prandtl hub-loss model? (flag)
TRUE                              TanInd - Include tangential induction in BEMT calculations? (flag)
FALSE                             AIDrag - Include the drag term in the axial-induction calculation? (flag)
FALSE                             TIDrag - Include the drag term in the tangential-induction calculation? (flag)
"DEFAULT"                       IndToler - Convergence tolerance for BEM induction factors (radians)
                 100             MaxIter - Maximum number of iteration steps (-)
======  Dynamic Blade-Element/Momentum Theory Options  ====================================================== [used only when WakeMod=2]
                   2           DBEMT_Mod - Type of dynamic BEMT (DBEMT) model (switch)
                   4          tau1_const - Time constant for DBEMT (s)
======  OLAF -- cOnvecting LAgrangian Filaments (Free Vortex Wake) Theory Options  ====================================================== [used only when WakeMod=3]
"UNUSED"               OLAFInputFileName - Input file for OLAF (file path)
======  Beddoes-Leishman Unsteady Aerofoil Aerodynamics Options  ===================================== [used only when AFAeroMod=2]
                   3               UAMod - Unsteady Aero Model Switch (switch)
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 aerofoil input files (flag) [used only when AFAeroMod=2] (flag)
======  Aerofoil Information =========================================================================
                   1            AFTabMod - Interpolation method for multiple airfoil tables (switch)
                   1          InCol_Alfa - The column in the aerofoil tables that contains the angle of attack (-)
                   2            InCol_Cl - The column in the aerofoil tables that contains the lift coefficient (-)
                   3            InCol_Cd - The column in the aerofoil tables that contains the drag coefficient (-)
                   4            InCol_Cm - The column in the aerofoil tables that contains the pitching-moment coefficient; use zero if there is no Cm column (-)
                   0         InCol_Cpmin - The column in the aerofoil tables that contains the drag coefficient; use zero if there is no Cpmin column (-)
                   8          NumAFfiles - Number of aerofoil files used (-)
"..\Aerofoils\Cylinder1_1000Hz.dat"             AfNames - Aerofoil file names (NumAFfiles lines) (file path)
"..\Aerofoils\Cylinder2_1000Hz.dat"
"..\Aerofoils\DU40_A17_1000Hz.dat"
"..\Aerofoils\DU35_A17_1000Hz.dat"
"..\Aerofoils\DU30_A17_1000Hz.dat"
"..\Aerofoils\DU25_A17_1000Hz.dat"
"..\Aerofoils\DU21_A17_1000Hz.dat"
"..\Aerofoils\NACA64_A17_1000Hz.dat"
======  Rotor Properties  ===========================================================================
TRUE                             UseBlCm - Include aerodynamic pitching moment in calculations? (flag)
"Blade.dat"                  ADBlFile(1) - Name of file containing distributed aerodynamic properties for Blade #1 (file path)
"Blade.dat"                  ADBlFile(2) - Name of file containing distributed aerodynamic properties for Blade #2 (file path)
"Blade.dat"                  ADBlFile(3) - Name of file containing distributed aerodynamic properties for Blade #3 [unused if NumBl < 3] (file path)
======  Tower Influence and Aerodynamics ============================================================= [used only when TwrPotent/=0, TwrShadow=True, or TwrAero=True]
                  11           NumTwrNds  - Number of tower nodes used in the analysis[used only when TwrInflnc/=0, or TwrAero=True] (-)
             TwrElev             TwrDiam               TwrCd               TwrTI
                 (m)                 (m)                 (-)                 (-)
       1.0000000E+01       6.5000000E+00       1.0000000E+00       1.0000000E-01
       1.7760000E+01       6.2400000E+00       1.0000000E+00       1.0000000E-01
       2.5520000E+01       5.9700000E+00       1.0000000E+00       1.0000000E-01
       3.3280000E+01       5.7100000E+00       1.0000000E+00       1.0000000E-01
       4.1040000E+01       5.4500000E+00       1.0000000E+00       1.0000000E-01
       4.8800000E+01       5.1800000E+00       1.0000000E+00       1.0000000E-01
       5.6560000E+01       4.9200000E+00       1.0000000E+00       1.0000000E-01
       6.4320000E+01       4.6600000E+00       1.0000000E+00       1.0000000E-01
       7.2080000E+01       4.4000000E+00       1.0000000E+00       1.0000000E-01
       7.9840000E+01       4.1300000E+00       1.0000000E+00       1.0000000E-01
       8.7600000E+01       3.8700000E+00       1.0000000E+00       1.0000000E-01
======  Outputs  ====================================================================================
FALSE                           SumPrint - Generate a summary file listing input options and interpolated properties to "<rootname>.AD.sum"? (flag)
                   8             NBlOuts - Number of blade node outputs [0 - 9] (-)
1, 2, 3, 4, 5, 6, 7, 8             BlOutNd - Blade nodes whose values will be output (-)
                   9             NTwOuts - Number of tower node outputs [0 - 9] (-)
3, 4, 5, 6, 7, 8, 9, 10, 11             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, (-)
"RtAeroPwr"                              ! Rotor aerodynamic power
"RtSpeed"                                ! Rotor speed
"TwN9VUndx"                              ! Undisturbed wind velocity at top of tower
"TwN1VUndx"                              ! Undisturbed wind velocity at base of tower
"RtAeroFxh"                              ! Rotor aerodynamic force Fx (wind direction)
"RtAeroFyh"                              ! Rotor aerodynamic force Fy (lateral direction)
"RtAeroFzh"                              ! Rotor aerodynamic force Fz (vertical direction)
"RtAeroMxh"                              ! Rotor aerodynamic moment Mx (roll direction)
"RtAeroMyh"                              ! Rotor aerodynamic moment My (pitch direction)
"RtAeroMzh"                              ! Rotor aerodynamic moment Mz (yaw direction)
END

ECHO file:

Echo file for AeroDyn 15 primary input file: <FILE PATH>
------- AERODYN v15.02.* INPUT FILE -----------------------------------------------------------------                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           
OC4 3.1 Modified (control system test)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          
======  General Options  ============================================================================                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           
 TRUE            = Echo                
 DEFAULT         = DTAero              
 1               = WakeMod             
 2               = AFAeroMod           
 1               = TwrPotent           
 0               = TwrShadow           
 TRUE            = TwrAero             
 FALSE           = FrozenWake          
 FALSE           = CavitCheck          
 FALSE           = CompAA              
 UNUSED          = AA_InputFile        
======  Environmental Conditions  ===================================================================                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           
 1.225           = AirDens             
 1.464E-05       = KinVisc             
 335             = SpdSound            
 103500          = Patm                
 1700            = Pvap                
 0.5             = FluidDepth          
======  Blade-Element/Momentum Theory Options  ====================================================== [used only when WakeMod=1]                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                
 2               = SkewMod             
 DEFAULT         = SkewModFactor       
 TRUE            = TipLoss             
 TRUE            = HubLoss             
 TRUE            = TanInd              
 FALSE           = AIDrag              
 FALSE           = TIDrag              
 DEFAULT         = IndToler            
 100             = MaxIter             
======  Dynamic Blade-Element/Momentum Theory Options  ====================================================== [used only when WakeMod=2]                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        
 2               = DBEMT_Mod           
 4               = tau1_const          
======  OLAF -- cOnvecting LAgrangian Filaments (Free Vortex Wake) Theory Options  ====================================================== [used only when WakeMod=3]                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            
 UNUSED          = OLAFInputFileName   
======  Beddoes-Leishman Unsteady Aerofoil Aerodynamics Options  ===================================== [used only when AFAeroMod=2]                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             
 3               = UAMod               
 TRUE            = FLookup             
======  Aerofoil Information =========================================================================                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          
 1               = AFTabMod            
 1               = InCol_Alfa          
 2               = InCol_Cl            
 3               = InCol_Cd            
 4               = InCol_Cm            
 0               = InCol_Cpmin         
 8               = NumAFfiles          
 ..\Aerofoils\Cy = AfNames             
 ..\Aerofoils\Cy =                     
 ..\Aerofoils\DU =                     
 ..\Aerofoils\DU =                     
 ..\Aerofoils\DU =                     
 ..\Aerofoils\DU =                     
 ..\Aerofoils\DU =                     
 ..\Aerofoils\NA =                     
======  Rotor Properties  ===========================================================================                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           
 TRUE            = UseBlCm             
 Blade.dat       = ADBlFile(1)         
 Blade.dat       = ADBlFile(2)         
 Blade.dat       = ADBlFile(3)         
======  Tower Influence and Aerodynamics ============================================================= [used only when TwrPotent/=0, TwrShadow=True, or TwrAero=True]                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           

Thank you,
Ashok

Thanks, @Ashok.Jammi

Could you also share the full message written to the command prompt when you execute OpenFAST v3.0?

Best regards,

Hi @Jason.Jonkman ,

Error: Init_AeroDyn:AD_Init:ParsePrimaryFileInfo:ParseLoVar:
>> A fatal error occurred when parsing data from <FILE PATH> 
>> The variable "SumPrint" was not found on line #62

Thank you,
Ashok

Dear @Ashok.Jammi,

Can you verify the exact version information for OpenFAST (at the very top of the output at the command line)? I am not able to reproduce your error with 3.0.0.

Regards,

Hi @Andy.Platt ,

yes it’s version 3.0.0.

@Jason.Jonkman ,

I see that from V3.0.0 - AeroDyn accepts multiple rotors. Does that affect input file in anyway ?

Dear @Ashok.Jammi,

Certainly the AeroDyn input file looks different if you are modeling multiple rotors through the standalone AeroDyn driver (as documented here: 4.2.1.6. AeroDyn Driver — OpenFAST v3.5.3 documentation), but the AeroDyn input file should be unchanged if you are only modeling a single rotor.

Best regards,