hi all, i'm a new user of Fluent. now i try to simulate 2-D supersonic wind tunnel (theoritically the velocity will start from subsonic, then accelerate to supersonic, then become subsonic again with occurence of normal/oblique shock) using inviscid model. i'm using pressure inlet, pressure outlet, and wall boundry conditions. the problem is that the solution is always divegence if i use coupled implicit. if i use coupled explicit, the residuals will osilate and never become converge. so what must i do now?

Try with pressure far field for your inlet and oulet boundary conditions.

hi cyril, i've used the pressure far field boundary condition, but the solutions never become converge. so what should i do?

Air flow through the engine intake valve(GDI) What is the best B.C to the model