I'm simulating a supersonic inlet by increasing the back pressure ratio. Till the the back pressure ratio of 4 at the interval of 1 I was able to generate results. When I'm simulating for back pressure ratio of 5 I couldn't solve and AMG solver is being detected.
Tried refining the mesh- didn't worked
Settings: altitude30km (corresponding P, T values) Mach :2.18 Desnity based solver Spalart–Allmaras turbulence model Explicit solver courant number -0.5
Hope I could find the solution. All suggestions are accepted