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#1 |
New Member
Jack Geoghegan
Join Date: Jan 2014
Posts: 3
Rep Power: 12 ![]() |
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! |
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Tags |
stall, unsteady, unsteady ; rotating, vlm |
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