[harishrajan96]

Hello All,

I am using Paraview for post processing a CFD simulation that I ran in OpenFOAM of a 3D wing. I am able to calculate the total lift and drag using extract block --> extract surface --> generate surface normals --> calculator --> integrate values method. However I want to run some structural analysis on the wing for which I need the lift/pressure distribution on the wing at discreet location along the span of the wing. I however do not know how to obtain this since I amd new to paraview and OpenFOAM. I would greatly appreciate any help towards this

Cheers !
Harish