Rocket Nozzle Question

It is my understanding that the exhaust of a rocket engine is a hypersonic flow which implies it is also a plasma, the physics of neither is properly accounted for in Solidworks Flow simulation. Further, you indicate that solid particles are present in the flow field which implies a multi phase flow, and again the physics of which are not provided for in flow simulation. Not to mention that combustion is also not modeled with Solidworks flow sim. It might be the case that a different code should be considered.