Source code for pymead.tutorials.mses_analysis
"""
This tutorial shows how the Pymead API can be used to run an MSES analysis on a NACA 23012 airfoil (automatically
downloaded from the web). See the code below or by
clicking on ``main`` under "Functions" at the bottom and then clicking [source] next to the ``main`` function.
.. highlight:: python
.. code-block:: python
import os
import tempfile
from pathlib import PureWindowsPath
from pymead.analysis.calc_aero_data import (calculate_aero_data, MSETSettings, MSESSettings, MPLOTSettings,
AirfoilMSETMeshingParameters)
from pymead.core.geometry_collection import GeometryCollection
def main():
# Create a geometry collection
geo_col = GeometryCollection()
# Download the airfoil and create an Airfoil object from it
polyline = geo_col.add_polyline(source="naca23012-il") # "source" can also be a file path
airfoil = polyline.add_polyline_airfoil()
# Create an MEA object from the airfoil (required for MSES analysis)
mea = geo_col.add_mea([airfoil])
# Configure the MSET settings (see the API reference for more options)
mset_settings = MSETSettings(
multi_airfoil_grid={"Airfoil-1": AirfoilMSETMeshingParameters()},
airfoil_side_points=180
)
# Configure the MSES settings (see the API reference for more options)
mses_settings = MSESSettings(
xtrs={"Airfoil-1": [1.0, 1.0]}, # This implies free transition;
# use values between 0.0 and 1.0 for forced transition
Ma=0.1,
Re=3.0e5,
Cl=0.7,
alfa_Cl_mode=1, # Should be set to 0 if "alfa" is specified instead
timeout=25.0 # The timeout for MSES in seconds
)
# Configure the MPLOT settings (see the API reference for more options)
mplot_settings = MPLOTSettings(
Tecplot=True # Export the flow field to the Tecplot ASCII .dat file format
)
print(f"Running MSES...")
aero_data, logs = calculate_aero_data(
conn=None, # Required argument
airfoil_coord_dir=tempfile.gettempdir(), # This can be changed to any directory
airfoil_name="naca23012", # This is the name of the analysis directory that gets created
mea=mea,
tool="MSES", # Must set this value since "XFOIL" is the default
mset_settings=mset_settings,
mses_settings=mses_settings,
mplot_settings=mplot_settings,
export_Cp=True, # This can be set to False if the pressure distributions are not needed
save_aero_data=True, # Setting this option to true exports a JSON file with the aerodynamic
# data available in the return statement
)
# Print a link to the output directory
analysis_dir = PureWindowsPath(os.path.normpath(os.path.abspath(os.path.dirname(logs['mset'])))).as_posix()
print(f"Output directory: file:///{analysis_dir}")
# Print the data
if not aero_data["converged"]:
raise ValueError("MSES did not converge")
if aero_data["errored_out"]:
raise ValueError("MSES errored out")
if aero_data["timed_out"]:
raise ValueError("MSES timed out")
print(f"Cl: {aero_data['Cl']:.2f} | Cd: {aero_data['Cd'] * 1e4:.2f} counts | Cm: {aero_data['Cm']:.3f}")
if __name__ == "__main__":
main()
"""
import os
import tempfile
from pathlib import PureWindowsPath
from pymead.analysis.calc_aero_data import (calculate_aero_data, MSETSettings, MSESSettings, MPLOTSettings,
AirfoilMSETMeshingParameters)
from pymead.core.geometry_collection import GeometryCollection
[docs]
def main():
# Create a geometry collection
geo_col = GeometryCollection()
# Download the airfoil and create an Airfoil object from it
polyline = geo_col.add_polyline(source="naca23012-il") # "source" can also be a file path
airfoil = polyline.add_polyline_airfoil()
# Create an MEA object from the airfoil (required for MSES analysis)
mea = geo_col.add_mea([airfoil])
# Configure the MSET settings (see the API reference for more options)
mset_settings = MSETSettings(
multi_airfoil_grid={"Airfoil-1": AirfoilMSETMeshingParameters()},
airfoil_side_points=180
)
# Configure the MSES settings (see the API reference for more options)
mses_settings = MSESSettings(
xtrs={"Airfoil-1": [1.0, 1.0]}, # This implies free transition;
# use values between 0.0 and 1.0 for forced transition
Ma=0.1,
Re=3.0e5,
Cl=0.7,
alfa_Cl_mode=1, # Should be set to 0 if "alfa" is specified instead
timeout=25.0 # The timeout for MSES in seconds
)
# Configure the MPLOT settings (see the API reference for more options)
mplot_settings = MPLOTSettings(
Tecplot=True # Export the flow field to the Tecplot ASCII .dat file format
)
print(f"Running MSES...")
aero_data, logs = calculate_aero_data(
conn=None, # Required argument
airfoil_coord_dir=tempfile.gettempdir(), # This can be changed to any directory
airfoil_name="naca23012", # This is the name of the analysis directory that gets created
mea=mea,
tool="MSES", # Must set this value since "XFOIL" is the default
mset_settings=mset_settings,
mses_settings=mses_settings,
mplot_settings=mplot_settings,
export_Cp=True, # This can be set to False if the pressure distributions are not needed
save_aero_data=True, # Setting this option to true exports a JSON file with the aerodynamic
# data available in the return statement
)
# Print a link to the output directory
analysis_dir = PureWindowsPath(os.path.normpath(os.path.abspath(os.path.dirname(logs['mset'])))).as_posix()
print(f"Output directory: file:///{analysis_dir}")
# Print the data
if not aero_data["converged"]:
raise ValueError("MSES did not converge")
if aero_data["errored_out"]:
raise ValueError("MSES errored out")
if aero_data["timed_out"]:
raise ValueError("MSES timed out")
print(f"Cl: {aero_data['Cl']:.2f} | Cd: {aero_data['Cd'] * 1e4:.2f} counts | Cm: {aero_data['Cm']:.3f}")
if __name__ == "__main__":
main()
