I am doing a project in which I need to analyze some airfoils at high speed (M 0.88) at a high altitude (51000 ft). I wanted to compare the results between the Spalart-Allmaras model and the SST k-w, which, if I understood correctly, are the right models for high-speed external flows. I am using ANSYS 2019 R1.
I have had no problem setting up the Spalart-Allmaras solver and the results I get are coherent. But when it comes to the SST k-w I am not able to prevent the solution from entering in ressonance, it looks like the averaged value would be correct but the solution does not converge. What are the setup options I should use for these transonic simulations?
Thanks in advance,
EDIT: I am analyzing a NACA 0012 at 0º. I am expecting a CD of around 0.08 to 0.1 (due to the shock waves) and a CL value of 0, as it is a symmetrical airfoil at 0º.