[Vishnu Sankar]

Hello there,

Using Python, I would like to directly extract the coefficient of lift and drag from a naca 0012 airfoil simulation, which is exactly same as the case in Quick Start . So I ran the Quick case by using the subprocess package in Python (code is attached below). I can see that the SCREEN_OUTPUT prints CL and CD values, but it seems the values are not stored anywhere. I want to know how can I directly extract the value of CL, CD from the solver using python. If not is there a way to save the CL, CD values to a .csv file directly? Any help is much appreciated.

Note: I tried out the pySU2 package, but I am running into an error and not sure how to proceed further. The issue is elaborated here

import subprocess
subprocess.run(' SU2_CFD inv_NACA0012.cfg', shell=True)

[bigfootedrockmidget]

You can find the values for lift and drag in the history output file:

https://su2code.github.io/docs_v7/Cu...history-output

You can use either the field name or the group output name

HISTORY_OUTPUT= ITER RMS_RES AERO_COEFF

[Vishnu Sankar]

Thanks a lot for your speedy response! I have another question: Is it not directly possible to extract the aerodynamic coefficients from the SU2 solver instead of writing it to an output file and then reading it? The reason why I am asking this is while performing a multidisciplinary optimization it is desirable for the optimizer to have a 'direct memory access' instead of using input/output files as the former savessignificant time,minimizes potential loss of accuracy and reduces storage space in disks.

[bigfootedrockmidget]

There are a couple of examples for the pywrapper in TestCases/py_wrapper, you can first run them to make sure that everything is working properly on your local machine (if you haven't done so already)