[songyi719]

Hi, I am running simulation for rocket at high altitude, which is low pressure & density condition with rhoCentralfoam.

For altitude of about 10km and M1.5, it works fine. However, as altitude and speed increases, solver aborts by several reasons.

First, it showed negative initial temperature, so I changed physicalproperties to janaf. Then, it showed sigFpe in omegawallfunction, so I changed it to laminar. Even then, time step decreased to somewhere like 1e-100 and aborted.

Is there tip for such supersonic flow solver? What could I do to converge the solution and get decent result?