[jackgeo]

Hi,

I was just wondering if anyone knows of a simple stall model (without calculating the boundary layer) that can be implemented in an unsteady vortex lattice method to compensate for a stalled section of the wing, or propeller blade.

Without increasing the computational efficiency, the only thing that springs to mind is a proportional drop in the overall chordwise circulation for a spanwise segment where the angle of attack exceeds the estimated stall angle.

If anyone has a better approach or reference to one thats already been published it would be greatly appreciated.

Cheers all!