Nozzle simulation for transitonal regime
 

Dear all,

I have started using dsmc Foam recenty. I have done the tutorials and I think i have understood to some degree how to simulate flow over bodies. However, I need to simulate the exhaust of a rocket nozzle in transitional regime. Going over some threads i realized that some people have worked on it. My question how come we do this in dsmc Foam. The people i contacted told me to develop my own solver using Bird's code.

A line in reply would be helpful.

Thanks and regards:)