Hello all,

Does somebody has solutions of commpressible flow ( non viscous) around general wing profile, in symmetric profile the atack angle can be in 2-3 degrees and small mach number for asymmetric profiles atack angle is 0 for example. if someone has the solution in Euler scheme it would be wonderful, It was told to me that the beam warming Algorithm is fine to this solution.

So if one can jelp me i will be very grateful

Hi,

Why do you look for a low mach number solution with a compressible code. You may experience convergence problems and/or spurious oscillations.

As for the Beam & Warming scheme, it can work well for Euler flows, but many schemes were designed since the BW one ... In the FVS family, you may try the Van Leer, AUSM+ and derivated, etc ... In particular, if you want to better describe shear flow areas, try newer schemes.

Regards