flow over rocket with plume
 

Hi everyone, I have been modeling external flow over a rocket. I have been using pressure_far_field b.c. and it works fine. I wish to run a simulation with the engine on (with plume). Any suggestions on what boundary condition to use to simulate the plume. I don't have too much info at the nozzle exit. I know engine thrust, impulse and can estimate exhaust velocity.

Appreciate any suggestions Thanks in advance Rouham