[Saima Khan]

Hey everyone, I need your suggestions regarding my simulation problem:

i am working on the 3D case of an atmosphere re-entry vehicle, the case is pure supersonic at Mach number 1.6 and angle of attack ranging from 140-170. Iam using density-based solver with an energy equation on. The problem is that for knowing the aerodynamic performance i am unable to get my desired results for my co-efficients of lift and drag. the major problem i am facing is either solution converges at just a few 1100 iterations or either it diverges.(showing temperature and then viscosity limitation)

my boundary conditions include pressure far-field for complete grid and wall for my vehicle. if anyone can please help me out in this case to get the right answer.