Hi! I am trying to simulate a hypersonic flow over wedge configuration. I have successfully simulated the flow problem at a subsonic Mach number (M=0.3). But increasing Mach number to a supersonic range, Let's say M=3, the solution diverges even with a decrease in time step size. I think my problem could be with the use of artificial viscosity or aliasing errors. Can somebody share the setup files for a supersonic case, maybe flow past NACA0012 airfoil test case from the user manual? And, any other suggestion or documentation relating to such a problem will be very helpful to me. Thank you Regards Gaurav Kumar Ph.D Student, Department of Aerospace Engineering, Indian Institute of Technology, Kanpur