Reply To: C-grid for airfoil simulation – High aspect ratios.

[sifislev17]

 

Hi again and thank you for your interest. I found a solution by creating an unstructured grid. I have some problems some time now though, I don’t know if you can help with that. I’m trying some time now to simulate flow over a 2D NACA0012 airfoil at Ma=0.85 and 2 degrees angle of attack and although residuals converge and all variables obtain accurate values, Cl refuses to converge or if it does (though not completely), it obtains completely inaccurate values. I have seen that the problem is that the location of the shock wave termination is wrong. Do you believe it is a mesh problem? I have tried different solvers and meshes but nothing works so far.