Hello: I am trying to simulate supersonic flow through a divergent nozzle, where the inlet is close to the throat region. I have only pressure boundaries as flow conditions, hence using the same to simulate the compressible flow. However facing problems with divergence, although have relaxed it quite a lot. I am using K-epsilon for turbulence and UD differencing scheme.

Need to know how to achieve convergence. Request your help in this regard. Thanks in advance - Mac.

please i need some information about the point of chocked

I am trying to simulate supersonic flow through a divergent nozzle, where the inlet is stable and then converging to the throat region. I have only pressure boundaries as flow conditions, hence using the same to simulate the compressible flow