[NumericalGuy]

Hi everyone,

I have a geometry of gliding vehicle which has a cylindrical body and large wings. I also have a mesh and results which are formed by someone else. I need to generate same results with geometry I have. I tried to generate similar surface mesh and I generated volume mesh with the same settings. Actually, my mesh quality is a little bit higher than old work. I also use same turbulence model (Spalart-Allmaras). And all other major settings are similar. I get solutions with different angle of attacks.

The problem is although I can generate similar results for angle of attacks b/w -8 to 6, beyond this range I cannot get similar results (Mach 0.5). The reason is flow separation occurs at wings beyond this range; however, flow separation does not exist previous solutions. I tried to do everything similar mesh, turbulence model, pressure based solver, ideal gas assumption etc. But I don't know what did I do differently from previous work which changes flow behavior.

Do you have any idea that can lead this important difference?