airfoil bending moment diagram
 

Hi,

I'm using simpleFoam to calculate forces and forceCoeffs of a 3D model of a wing (eppler420 profile airfoil), under different angles of attack and wind velocities.

Now I want to obtain bending and torsion moments along the airfoil span (as a cantilever beam).

I guess it may have relation with functions patchIntegrate and wallShearStress, buy I don't know how do it.

I imagine the process by taking the pressure integral of thin transversal sections of the airfoil and multiply the resultant force by the corresponding distance, thus obtaining the bending moment diagram of the wing. And in a similar way obtain the wing torsion diagram as well.

Is it necessary to program such algorithm, maybe modifying patchIntegrate?

Or maybe wing bending moment and torsion moment diagrams can be worked out using paraFoam or paraView?

Any suggestion will be very welcome!
Thank's a lot,

Lluis