Boundary Layer Setup Compressible hypersonic flow
I am trying to simulate the airflow around a 2D-wedge which is moving at hypersonic speed (Mach=8 at 30000 m).
I understand and have read that for my application pressure inlet, pressure outlet and pressure farfield boundary conditions are applicable.
My problem is that my solution won't converge at all. I have tried changing the boundary conditions and the solution methods, switching on and off the turbulence modeling and so on.
Here are my settings:
Fluid: Air: Density ideal-gas and viscosity according to sutherland law
Inlet: Pressure inlet: I calculated a total pressure of p(total) = 2.93e8 Pa (isentropic relation with Ratio of Specific Heats = 1.4, Ma=8 and p(static, 30000 m, ISA)=301hPa. I set the "Gauge Total Pressure" to my calculated total pressure value. The "Supersonic/Initial Gauge Presse" I set to my p(static). The temperature is 228.75 K (ISA, 30000 m)
Outlet: Pressure outlet: Here I set the "Gauge Pressure" to the aforementioned p(static) = 301hPa and the Temperature to 228.75 K.
The outer "walls" defined as pressure far field BoC: Ma = 8 and Gauge pressure to p(static) = 301hPa.
I also set the "Operating Pressure" to 0.
Implicit, Roe-FDS, Gradient: Least Squares, Flow, Turbulent Kinetic Energy and Specifiy Dissipation Rate: Second Order Upwind
Now first of all as I mentioned the solution doesn't converge at all. Then when I check the Reference Values, I see that the calculated velocity in the inlet doesn't represent the numbers I would have expected.
I would be very thankful if you could help me find the solution for my problem. I am new to CFD/Ansys which is why I want to gain as much knowledge as possible.
Thank you very much.