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Openfast io (#417)
* Switch to openfast_io and update to OpenFAST v4.0.0 * Remove old IEA-UMaineSemi, move linearizations * Revert ROSCO_Testing exes * Start updating NREL-5MW model * Examples working except 5,7,14,17,26 * working example 26 * Enable yaw control * Add openfast_io to pip installs * Install openfast 4.0 in CI * Install openfast_io in toml * Print pytest outputs * Update IEA-15 Semi paths * Search for servodyn files recursively * Fix paths in tests, update discon script * Update discons * Increase tolerance on check, checkpoint not perfect * Skip python 3.9 * Fix path in notebook * try newer conda packages * add zmq explicitly * another try * more debug * Try m2-pkg-config * Update install.rst --------- Co-authored-by: Mayank Chetan <[email protected]> Co-authored-by: Garrett Barter <[email protected]>
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‎.github/workflows/CI_rosco-compile.yml

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@@ -17,7 +17,7 @@ jobs:
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fail-fast: false #true
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matrix:
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os: ["ubuntu-latest", "macOS-latest", "windows-latest"] #mac-13 intel, mac-14 arm
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python-version: ["3.9", "3.10", "3.11", "3.12"]
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python-version: ["3.10", "3.11", "3.12"]
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steps:
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- name: Setup GNU Fortran
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strategy:
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fail-fast: false #true
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matrix:
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os: ["ubuntu-latest", "macOS-13", "windows-latest"] #mac-13 intel, mac-14 arm
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python-version: ["3.9", "3.10", "3.11", "3.12"]
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os: ["ubuntu-latest", "macOS-13", "macOS-14", "windows-latest"] #mac-13 intel, mac-14 arm
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python-version: ["3.10", "3.11", "3.12"]
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steps:
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- name: checkout repository
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uses: actions/checkout@v4
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- uses: conda-incubator/setup-miniconda@v2
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- uses: conda-incubator/setup-miniconda@v3
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# https://github.com/marketplace/actions/setup-miniconda
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with:
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#mamba-version: "*"
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miniforge-version: "latest"
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auto-update-conda: true
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python-version: ${{ matrix.python-version }}
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environment-file: environment.yml
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activate-environment: test
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auto-activate-base: false
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- name: Install OpenFAST
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run: |
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conda install openfast>=4.0
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- name: Add dependencies windows specific
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if: contains( matrix.os, 'windows')
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run: |
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conda install -y m2w64-toolchain libpython
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conda install -y gfortran gcc libpython m2-pkg-config
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gfortran --version
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ls C:/Users/runneradmin/miniconda3/envs/test/Library/lib/*zmq*
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- name: Add dependencies mac specific
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if: contains( matrix.os, 'mac')
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- name: Debug
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run: |
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conda list
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printenv
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printenv | sort
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- name: Conda Install ROSCO
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run: |
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python -m pip install -e .
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- name: Install OpenFAST
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run: |
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conda install openfast==3.5.3
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python -m pip install -e . --no-build-isolation
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- name: Generate Registry
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run: |
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if: contains( matrix.os, 'ubuntu')
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run: |
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cd rosco/test
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pytest .
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pytest -s .
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- name: Test walkthrough notebook
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if: contains( matrix.os, 'ubuntu')

‎.gitignore

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@@ -82,6 +82,7 @@ Examples/*.p
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# Exclude testing results
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ROSCO_testing/results/
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ROSCO_testing/testing
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rosco/test/testing
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# Simulink/Matlab temp files
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*.slxc

‎Examples/.gitignore

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Cp_Ct_Cq.*.txt
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*.p
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examples_out/
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examples_out/
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11_robust_tuning_out
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*.10

‎Examples/05_openfast_sim.py

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@@ -23,6 +23,7 @@
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from rosco.toolbox import turbine as ROSCO_turbine
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from rosco.toolbox.utilities import write_DISCON, run_openfast
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from rosco.toolbox.inputs.validation import load_rosco_yaml
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from rosco import discon_lib_path
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def main():
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this_dir = os.path.dirname(os.path.abspath(__file__))
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txt_filename=os.path.join(tune_dir,path_params['rotor_performance_filename'])
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)
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# Setting up the location of ROSCO library
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turbine.fast.fst_vt['ServoDyn']['DLL_FileName'] = discon_lib_path
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# Tune controller
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controller.tune_controller(turbine)
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‎Examples/07_openfast_outputs.py

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@@ -25,7 +25,7 @@ def main():
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os.makedirs(example_out_dir)
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# Define openfast output filenames
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filenames = ["Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT-UMaineSemi.outb"]
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filenames = ["Test_Cases/IEA-15-240-RWT/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT-UMaineSemi.outb"]
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# ---- Note: Could load and plot multiple cases, textfiles, and binaries...
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# filenames = ["../Test_Cases/NREL-5MW/NREL-5MW.outb",
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# "../Test_Cases/NREL-5MW/NREL-5MW_ex8.outb"]

‎Examples/14_open_loop_control.py

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### Run OpenFAST using aeroelasticse tools
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case_inputs = {}
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case_inputs[('ServoDyn','DLL_FileName')] = {'vals': [discon_lib_path], 'group': 0}
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case_inputs[('ServoDyn','Ptch_Cntrl')] = {'vals': [1], 'group': 0}
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case_inputs[('ServoDyn','YCMode')] = {'vals': [5], 'group': 0}
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case_inputs[('ServoDyn','TYCOn')] = {'vals': [0], 'group': 0}
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case_inputs[('ElastoDyn','YawDOF')] = {'vals': ['True'], 'group': 0}
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# Apply all discon variables as case inputs
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discon_vt = ROSCO_utilities.DISCON_dict(

‎Examples/22_cable_control.py

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@@ -19,7 +19,7 @@
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from rosco.toolbox.ofTools.case_gen import CaseLibrary as cl
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from rosco.toolbox.ofTools.fast_io import output_processing
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import numpy as np
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from rosco.toolbox.ofTools.fast_io.FAST_reader import InputReader_OpenFAST
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from openfast_io.FAST_reader import InputReader_OpenFAST
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from rosco.toolbox.inputs.validation import load_rosco_yaml
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import matplotlib.pyplot as plt
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from rosco.toolbox.controller import OpenLoopControl

‎Examples/23_structural_control.py

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@@ -19,7 +19,7 @@
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from rosco.toolbox.ofTools.case_gen.run_FAST import run_FAST_ROSCO
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from rosco.toolbox.ofTools.case_gen import CaseLibrary as cl
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#import numpy as np
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from rosco.toolbox.ofTools.fast_io.FAST_reader import InputReader_OpenFAST
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from openfast_io.FAST_reader import InputReader_OpenFAST
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from rosco.toolbox.inputs.validation import load_rosco_yaml
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from rosco.toolbox.controller import OpenLoopControl
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reader.execute()
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reader.fst_vt['ServoDyn']['NumSStC'] = 3
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reader.fst_vt['ServoDyn']['SStCfiles'] = ['StC-Force-Col1.dat', 'StC-Force-Col2.dat', 'StC-Force-Col3.dat']
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reader.fst_vt['ServoDyn']['SStCfiles'] = ['../StC-Force-Col1.dat', '../StC-Force-Col2.dat', '../StC-Force-Col3.dat']
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# Add SStC file inputs
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for StC_file in reader.fst_vt['ServoDyn']['SStCfiles']:
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reader.fst_vt['SStC'].append(reader.read_StC(StC_file))

‎Examples/28_tower_resonance.py

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from rosco.toolbox.ofTools.case_gen.run_FAST import run_FAST_ROSCO
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from rosco.toolbox.ofTools.case_gen import CaseLibrary as cl
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#from rosco.toolbox.ofTools.fast_io import output_processing
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from rosco.toolbox.ofTools.fast_io.FAST_reader import InputReader_OpenFAST
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from openfast_io.FAST_reader import InputReader_OpenFAST
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from rosco.toolbox.inputs.validation import load_rosco_yaml
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import numpy as np

‎Examples/ROSCO_walkthrough.ipynb

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"\n",
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"# Define openfast output filenames, please fill in your own .outb\n",
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"# filenames = [\"../Test_Cases/5MW_Step/5MW_Step.outb\"]\n",
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"filenames = ['Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT-UMaineSemi.outb']\n",
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"filenames = ['Test_Cases/IEA-15-240-RWT/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT-UMaineSemi.outb']\n",
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"# Load output info and data\n",
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"fast_out = op.load_fast_out(filenames)\n",
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"\n",

‎Examples/Test_Cases/BAR_10/Airfoils/BAR_10_AeroDyn15_Polar_00.dat

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@@ -7,12 +7,12 @@ DEFAULT InterpOrd ! Interpolation order to use for quasi-stea
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1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded)
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@"AF00_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included.
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AF00_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called.
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1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl.
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1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and UserProp.
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! ------------------------------------------------------------------------------
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! data for table 1
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! ------------------------------------------------------------------------------
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0.754030 Re ! Reynolds number in millions
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0 Ctrl ! Control setting (must be 0 for current AirfoilInfo)
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0 UserProp ! Control setting (must be 0 for current AirfoilInfo)
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True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line
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!........................................
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29.393939 alpha0 ! 0-lift angle of attack, depends on airfoil.

‎Examples/Test_Cases/BAR_10/Airfoils/BAR_10_AeroDyn15_Polar_01.dat

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1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded)
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@"AF01_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included.
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AF01_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called.
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1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl.
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1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and UserProp.
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! ------------------------------------------------------------------------------
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! data for table 1
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! ------------------------------------------------------------------------------
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1.626654 Re ! Reynolds number in millions
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0 Ctrl ! Control setting (must be 0 for current AirfoilInfo)
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0 UserProp ! Control setting (must be 0 for current AirfoilInfo)
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True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line
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!........................................
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2.107816 alpha0 ! 0-lift angle of attack, depends on airfoil.

‎Examples/Test_Cases/BAR_10/Airfoils/BAR_10_AeroDyn15_Polar_02.dat

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1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded)
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@"AF02_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included.
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AF02_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called.
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1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl.
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1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and UserProp.
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! ------------------------------------------------------------------------------
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! data for table 1
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! ------------------------------------------------------------------------------
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2.538528 Re ! Reynolds number in millions
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0 Ctrl ! Control setting (must be 0 for current AirfoilInfo)
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0 UserProp ! Control setting (must be 0 for current AirfoilInfo)
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True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line
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!........................................
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1.985575 alpha0 ! 0-lift angle of attack, depends on airfoil.

‎Examples/Test_Cases/BAR_10/Airfoils/BAR_10_AeroDyn15_Polar_03.dat

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1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded)
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@"AF03_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included.
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AF03_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called.
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1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl.
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1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and UserProp.
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! ------------------------------------------------------------------------------
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! data for table 1
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! ------------------------------------------------------------------------------
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3.518213 Re ! Reynolds number in millions
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0 Ctrl ! Control setting (must be 0 for current AirfoilInfo)
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0 UserProp ! Control setting (must be 0 for current AirfoilInfo)
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True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line
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!........................................
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1.807510 alpha0 ! 0-lift angle of attack, depends on airfoil.

‎Examples/Test_Cases/BAR_10/Airfoils/BAR_10_AeroDyn15_Polar_04.dat

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1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded)
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@"AF04_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included.
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AF04_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called.
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1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl.
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1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and UserProp.
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! ------------------------------------------------------------------------------
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! data for table 1
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! ------------------------------------------------------------------------------
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4.575668 Re ! Reynolds number in millions
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0 Ctrl ! Control setting (must be 0 for current AirfoilInfo)
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0 UserProp ! Control setting (must be 0 for current AirfoilInfo)
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True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line
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!........................................
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1.678026 alpha0 ! 0-lift angle of attack, depends on airfoil.

‎Examples/Test_Cases/BAR_10/Airfoils/BAR_10_AeroDyn15_Polar_05.dat

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1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded)
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@"AF05_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included.
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AF05_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called.
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1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl.
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1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and UserProp.
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! ------------------------------------------------------------------------------
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! data for table 1
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! ------------------------------------------------------------------------------
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5.700528 Re ! Reynolds number in millions
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0 Ctrl ! Control setting (must be 0 for current AirfoilInfo)
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0 UserProp ! Control setting (must be 0 for current AirfoilInfo)
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True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line
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!........................................
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1.619305 alpha0 ! 0-lift angle of attack, depends on airfoil.

‎Examples/Test_Cases/BAR_10/Airfoils/BAR_10_AeroDyn15_Polar_06.dat

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1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded)
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@"AF06_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included.
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AF06_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called.
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1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl.
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1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and UserProp.
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! ------------------------------------------------------------------------------
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! data for table 1
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! ------------------------------------------------------------------------------
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6.865415 Re ! Reynolds number in millions
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0 Ctrl ! Control setting (must be 0 for current AirfoilInfo)
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0 UserProp ! Control setting (must be 0 for current AirfoilInfo)
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True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line
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!........................................
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1.063866 alpha0 ! 0-lift angle of attack, depends on airfoil.

‎Examples/Test_Cases/BAR_10/Airfoils/BAR_10_AeroDyn15_Polar_07.dat

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@@ -7,12 +7,12 @@ DEFAULT InterpOrd ! Interpolation order to use for quasi-stea
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1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded)
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@"AF07_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included.
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AF07_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called.
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1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl.
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1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and UserProp.
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! ------------------------------------------------------------------------------
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! data for table 1
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! ------------------------------------------------------------------------------
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8.026545 Re ! Reynolds number in millions
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0 Ctrl ! Control setting (must be 0 for current AirfoilInfo)
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0 UserProp ! Control setting (must be 0 for current AirfoilInfo)
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True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line
1717
!........................................
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-0.252813 alpha0 ! 0-lift angle of attack, depends on airfoil.

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