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#41 |
Member
james nathman
Join Date: May 2011
Posts: 62
Rep Power: 15 ![]() |
This movie.
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#42 |
New Member
amin95
Join Date: Jul 2019
Posts: 20
Rep Power: 7 ![]() |
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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#43 |
Member
Zack
Join Date: Dec 2015
Location: uk
Posts: 34
Rep Power: 10 ![]() |
Actually I am writing panel method code for flow separation as well.
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#44 |
New Member
amin95
Join Date: Jul 2019
Posts: 20
Rep Power: 7 ![]() |
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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Tags |
boundary element method, panel method |
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