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Switch to openfast_io and update to OpenFAST v4.0.0 #415

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Switch to openfast_io and update to OpenFAST v4.0.0 #415

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f9e35be
Switch to openfast_io and update to OpenFAST v4.0.0
mayankchetan Jan 12, 2025
5a15183
Remove old IEA-UMaineSemi, move linearizations
dzalkind Jan 14, 2025
26e64f6
Revert ROSCO_Testing exes
dzalkind Jan 14, 2025
a83325b
Start updating NREL-5MW model
dzalkind Jan 14, 2025
bb73bec
Examples working except 5,7,14,17,26
mayankchetan Jan 15, 2025
f49c179
working example 26
mayankchetan Jan 16, 2025
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1 change: 1 addition & 0 deletions .gitignore
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Expand Up @@ -82,6 +82,7 @@ Examples/*.p
# Exclude testing results
ROSCO_testing/results/
ROSCO_testing/testing
rosco/test/testing

# Simulink/Matlab temp files
*.slxc
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5 changes: 3 additions & 2 deletions Examples/.gitignore
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@@ -1,3 +1,4 @@
Cp_Ct_Cq.*.txt
*.p
examples_out/
examples_out/
11_robust_tuning_out
*.10
4 changes: 4 additions & 0 deletions Examples/05_openfast_sim.py
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Expand Up @@ -23,6 +23,7 @@
from rosco.toolbox import turbine as ROSCO_turbine
from rosco.toolbox.utilities import write_DISCON, run_openfast
from rosco.toolbox.inputs.validation import load_rosco_yaml
from rosco import discon_lib_path

def main():
this_dir = os.path.dirname(os.path.abspath(__file__))
Expand All @@ -48,6 +49,9 @@ def main():
txt_filename=os.path.join(tune_dir,path_params['rotor_performance_filename'])
)

# Setting up the location of ROSCO library
turbine.fast.fst_vt['ServoDyn']['DLL_FileName'] = discon_lib_path

# Tune controller
controller.tune_controller(turbine)

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1 change: 1 addition & 0 deletions Examples/14_open_loop_control.py
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Expand Up @@ -91,6 +91,7 @@ def main():
### Run OpenFAST using aeroelasticse tools
case_inputs = {}
case_inputs[('ServoDyn','DLL_FileName')] = {'vals': [discon_lib_path], 'group': 0}
case_inputs[('ServoDyn','Ptch_Cntrl')] = {'vals': [1], 'group': 0}

# Apply all discon variables as case inputs
discon_vt = ROSCO_utilities.DISCON_dict(
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2 changes: 1 addition & 1 deletion Examples/22_cable_control.py
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Expand Up @@ -19,7 +19,7 @@
from rosco.toolbox.ofTools.case_gen import CaseLibrary as cl
from rosco.toolbox.ofTools.fast_io import output_processing
import numpy as np
from rosco.toolbox.ofTools.fast_io.FAST_reader import InputReader_OpenFAST
from openfast_io.FAST_reader import InputReader_OpenFAST
from rosco.toolbox.inputs.validation import load_rosco_yaml
import matplotlib.pyplot as plt
from rosco.toolbox.controller import OpenLoopControl
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4 changes: 2 additions & 2 deletions Examples/23_structural_control.py
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Expand Up @@ -19,7 +19,7 @@
from rosco.toolbox.ofTools.case_gen.run_FAST import run_FAST_ROSCO
from rosco.toolbox.ofTools.case_gen import CaseLibrary as cl
#import numpy as np
from rosco.toolbox.ofTools.fast_io.FAST_reader import InputReader_OpenFAST
from openfast_io.FAST_reader import InputReader_OpenFAST
from rosco.toolbox.inputs.validation import load_rosco_yaml
from rosco.toolbox.controller import OpenLoopControl

Expand Down Expand Up @@ -47,7 +47,7 @@ def main():
reader.execute()

reader.fst_vt['ServoDyn']['NumSStC'] = 3
reader.fst_vt['ServoDyn']['SStCfiles'] = ['StC-Force-Col1.dat', 'StC-Force-Col2.dat', 'StC-Force-Col3.dat']
reader.fst_vt['ServoDyn']['SStCfiles'] = ['../StC-Force-Col1.dat', '../StC-Force-Col2.dat', '../StC-Force-Col3.dat']
# Add SStC file inputs
for StC_file in reader.fst_vt['ServoDyn']['SStCfiles']:
reader.fst_vt['SStC'].append(reader.read_StC(StC_file))
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2 changes: 1 addition & 1 deletion Examples/28_tower_resonance.py
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Expand Up @@ -9,7 +9,7 @@
from rosco.toolbox.ofTools.case_gen.run_FAST import run_FAST_ROSCO
from rosco.toolbox.ofTools.case_gen import CaseLibrary as cl
#from rosco.toolbox.ofTools.fast_io import output_processing
from rosco.toolbox.ofTools.fast_io.FAST_reader import InputReader_OpenFAST
from openfast_io.FAST_reader import InputReader_OpenFAST
from rosco.toolbox.inputs.validation import load_rosco_yaml

import numpy as np
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4 changes: 2 additions & 2 deletions Examples/Test_Cases/BAR_10/Airfoils/BAR_10_AeroDyn15_Polar_00.dat
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Expand Up @@ -7,12 +7,12 @@ DEFAULT InterpOrd ! Interpolation order to use for quasi-stea
1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded)
@"AF00_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included.
AF00_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called.
1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl.
1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and UserProp.
! ------------------------------------------------------------------------------
! data for table 1
! ------------------------------------------------------------------------------
0.754030 Re ! Reynolds number in millions
0 Ctrl ! Control setting (must be 0 for current AirfoilInfo)
0 UserProp ! Control setting (must be 0 for current AirfoilInfo)
True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line
!........................................
29.393939 alpha0 ! 0-lift angle of attack, depends on airfoil.
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4 changes: 2 additions & 2 deletions Examples/Test_Cases/BAR_10/Airfoils/BAR_10_AeroDyn15_Polar_01.dat
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Expand Up @@ -7,12 +7,12 @@ DEFAULT InterpOrd ! Interpolation order to use for quasi-stea
1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded)
@"AF01_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included.
AF01_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called.
1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl.
1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and UserProp.
! ------------------------------------------------------------------------------
! data for table 1
! ------------------------------------------------------------------------------
1.626654 Re ! Reynolds number in millions
0 Ctrl ! Control setting (must be 0 for current AirfoilInfo)
0 UserProp ! Control setting (must be 0 for current AirfoilInfo)
True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line
!........................................
2.107816 alpha0 ! 0-lift angle of attack, depends on airfoil.
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4 changes: 2 additions & 2 deletions Examples/Test_Cases/BAR_10/Airfoils/BAR_10_AeroDyn15_Polar_02.dat
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Expand Up @@ -7,12 +7,12 @@ DEFAULT InterpOrd ! Interpolation order to use for quasi-stea
1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded)
@"AF02_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included.
AF02_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called.
1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl.
1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and UserProp.
! ------------------------------------------------------------------------------
! data for table 1
! ------------------------------------------------------------------------------
2.538528 Re ! Reynolds number in millions
0 Ctrl ! Control setting (must be 0 for current AirfoilInfo)
0 UserProp ! Control setting (must be 0 for current AirfoilInfo)
True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line
!........................................
1.985575 alpha0 ! 0-lift angle of attack, depends on airfoil.
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4 changes: 2 additions & 2 deletions Examples/Test_Cases/BAR_10/Airfoils/BAR_10_AeroDyn15_Polar_03.dat
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Expand Up @@ -7,12 +7,12 @@ DEFAULT InterpOrd ! Interpolation order to use for quasi-stea
1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded)
@"AF03_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included.
AF03_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called.
1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl.
1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and UserProp.
! ------------------------------------------------------------------------------
! data for table 1
! ------------------------------------------------------------------------------
3.518213 Re ! Reynolds number in millions
0 Ctrl ! Control setting (must be 0 for current AirfoilInfo)
0 UserProp ! Control setting (must be 0 for current AirfoilInfo)
True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line
!........................................
1.807510 alpha0 ! 0-lift angle of attack, depends on airfoil.
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4 changes: 2 additions & 2 deletions Examples/Test_Cases/BAR_10/Airfoils/BAR_10_AeroDyn15_Polar_04.dat
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Expand Up @@ -7,12 +7,12 @@ DEFAULT InterpOrd ! Interpolation order to use for quasi-stea
1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded)
@"AF04_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included.
AF04_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called.
1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl.
1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and UserProp.
! ------------------------------------------------------------------------------
! data for table 1
! ------------------------------------------------------------------------------
4.575668 Re ! Reynolds number in millions
0 Ctrl ! Control setting (must be 0 for current AirfoilInfo)
0 UserProp ! Control setting (must be 0 for current AirfoilInfo)
True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line
!........................................
1.678026 alpha0 ! 0-lift angle of attack, depends on airfoil.
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4 changes: 2 additions & 2 deletions Examples/Test_Cases/BAR_10/Airfoils/BAR_10_AeroDyn15_Polar_05.dat
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Expand Up @@ -7,12 +7,12 @@ DEFAULT InterpOrd ! Interpolation order to use for quasi-stea
1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded)
@"AF05_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included.
AF05_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called.
1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl.
1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and UserProp.
! ------------------------------------------------------------------------------
! data for table 1
! ------------------------------------------------------------------------------
5.700528 Re ! Reynolds number in millions
0 Ctrl ! Control setting (must be 0 for current AirfoilInfo)
0 UserProp ! Control setting (must be 0 for current AirfoilInfo)
True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line
!........................................
1.619305 alpha0 ! 0-lift angle of attack, depends on airfoil.
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4 changes: 2 additions & 2 deletions Examples/Test_Cases/BAR_10/Airfoils/BAR_10_AeroDyn15_Polar_06.dat
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Expand Up @@ -7,12 +7,12 @@ DEFAULT InterpOrd ! Interpolation order to use for quasi-stea
1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded)
@"AF06_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included.
AF06_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called.
1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl.
1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and UserProp.
! ------------------------------------------------------------------------------
! data for table 1
! ------------------------------------------------------------------------------
6.865415 Re ! Reynolds number in millions
0 Ctrl ! Control setting (must be 0 for current AirfoilInfo)
0 UserProp ! Control setting (must be 0 for current AirfoilInfo)
True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line
!........................................
1.063866 alpha0 ! 0-lift angle of attack, depends on airfoil.
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4 changes: 2 additions & 2 deletions Examples/Test_Cases/BAR_10/Airfoils/BAR_10_AeroDyn15_Polar_07.dat
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Expand Up @@ -7,12 +7,12 @@ DEFAULT InterpOrd ! Interpolation order to use for quasi-stea
1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded)
@"AF07_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included.
AF07_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called.
1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl.
1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and UserProp.
! ------------------------------------------------------------------------------
! data for table 1
! ------------------------------------------------------------------------------
8.026545 Re ! Reynolds number in millions
0 Ctrl ! Control setting (must be 0 for current AirfoilInfo)
0 UserProp ! Control setting (must be 0 for current AirfoilInfo)
True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line
!........................................
-0.252813 alpha0 ! 0-lift angle of attack, depends on airfoil.
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4 changes: 2 additions & 2 deletions Examples/Test_Cases/BAR_10/Airfoils/BAR_10_AeroDyn15_Polar_08.dat
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Expand Up @@ -7,12 +7,12 @@ DEFAULT InterpOrd ! Interpolation order to use for quasi-stea
1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded)
@"AF08_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included.
AF08_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called.
1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl.
1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and UserProp.
! ------------------------------------------------------------------------------
! data for table 1
! ------------------------------------------------------------------------------
9.120474 Re ! Reynolds number in millions
0 Ctrl ! Control setting (must be 0 for current AirfoilInfo)
0 UserProp ! Control setting (must be 0 for current AirfoilInfo)
True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line
!........................................
-1.292496 alpha0 ! 0-lift angle of attack, depends on airfoil.
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4 changes: 2 additions & 2 deletions Examples/Test_Cases/BAR_10/Airfoils/BAR_10_AeroDyn15_Polar_09.dat
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Expand Up @@ -7,12 +7,12 @@ DEFAULT InterpOrd ! Interpolation order to use for quasi-stea
1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded)
@"AF09_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included.
AF09_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called.
1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl.
1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and UserProp.
! ------------------------------------------------------------------------------
! data for table 1
! ------------------------------------------------------------------------------
10.036688 Re ! Reynolds number in millions
0 Ctrl ! Control setting (must be 0 for current AirfoilInfo)
0 UserProp ! Control setting (must be 0 for current AirfoilInfo)
True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line
!........................................
-1.701696 alpha0 ! 0-lift angle of attack, depends on airfoil.
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4 changes: 2 additions & 2 deletions Examples/Test_Cases/BAR_10/Airfoils/BAR_10_AeroDyn15_Polar_10.dat
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Expand Up @@ -7,12 +7,12 @@ DEFAULT InterpOrd ! Interpolation order to use for quasi-stea
1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded)
@"AF10_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included.
AF10_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called.
1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl.
1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and UserProp.
! ------------------------------------------------------------------------------
! data for table 1
! ------------------------------------------------------------------------------
10.740662 Re ! Reynolds number in millions
0 Ctrl ! Control setting (must be 0 for current AirfoilInfo)
0 UserProp ! Control setting (must be 0 for current AirfoilInfo)
True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line
!........................................
-2.060294 alpha0 ! 0-lift angle of attack, depends on airfoil.
Expand Down
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