[Ready33]

Hello,

I need to simulate nozzle of rocket engine with solid propellant.

Inside (inlet) parameters are very high (pressure about 13,5 MPa, temperature about 2200°C, velocity about 950 m/s, density about 17,34 kg/m3) and it flows to (outlet) standard atmosphere (i.e. 101 kPa, ~ 25°C, 0 m/s, density 1,1 kg/m3).

I have tried some solvers (rhoPimpleFoam, rhoCentralFoam etc.), some combinations of initial and boundary conditions, some different geometries and do not succeed. Simulations failed or give crazy results.

Do you have any idea how to solve this task?

Thanks

Radek