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3D Panel Method Code

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Old   September 23, 2019, 18:35
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james nathman
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This movie.
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Old   September 23, 2019, 19:45
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Thanks for your reply.

I could manage to solve the problem. It was a numerical error within MATLAB while calculating influence coefficients. Changing range of atan2 from [-pi,+pi] to [0,+2pi] with MATLAB's mode function had caused numerical errors.

I'd like to ask some questions if you don't mind.
1) Is double wake method good for simulating post stall flows over wings?
2) How could i simply model a wing's aileron with 3d panel method ?
3) Could wake panels go through a body surface without causing problem? (for example when wing's wake in an aircraft face rear vertical and horizontal stabilizers surface)
4) Could i use Dirichlet boundary conditions for lifting parts and Neumann boundary condition for non lifting parts simultaneously in 3d panel method?

Best Regards
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Old   September 24, 2019, 09:32
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Actually I am writing panel method code for flow separation as well.
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Old   September 24, 2019, 15:58
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Well then, maybe we could help each other. Which method you use for modelling flow separation of post stall? Double wake, Decambering or ...
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