I would like to know how to calculate the aerodynamic forces (Fx, Fy, Fz) and moments on a wing surface using integration with Python, an example of how my data in the *.CSV file looks like:
| X_coordinate | Y_coordinate | Z_coordinate | Pressure | X_normals | Y_normals | Z_normals |
|---|---|---|---|---|---|---|
| 2.34979 | 0 | 5.01509 | 0.989625 | -0.981281 | 0.188252 | -0.0406009 |
| 2.3516 | 0 | 5.07262 | 0.979072 | -0.978972 | 0.188853 | 0.0771268 |
| 2.35503 | 0 | 4.95777 | 0.984588 | -0.971282 | 0.180498 | -0.155022 |
| 2.36013 | 0 | 5.12954 | 0.954055 | -0.963974 | 0.183935 | 0.192153 |
| 2.36676 | 0 | 4.90141 | 0.964809 | -0.950169 | 0.16695 | -0.26326 |
| 2.37934 | 0.150177 | 4.99971 | 0.971161 | -0.940029 | 0.337158 | -0.0516759 |
| 2.38006 | 0.151914 | 5.06327 | 0.963597 | -0.939053 | 0.338328 | 0.0609358 |
| 2.37493 | 0 | 5.18517 | 0.919066 | -0.938548 | 0.175529 | 0.297181 |
| 2.38563 | 0.147054 | 4.93709 | 0.96491 | -0.93166 | 0.326119 | -0.160173 |
I'm aware of how to do it with Tecplot 360 (link) and Paraview but would appreciate it if anyone could help me do the same with Python. Thanks.