[TommyM]

Hi All,


I am trying to simulate the flow (inviscid and laminar) inside a rocket nozzle with rhoPimpleFoam, but all my simulations crash.
I think my boundary conditions are the cause of this crash (my BCs are attached in the .zip folder). Maybe, they are ill-posed.
Does anyone know what kind of boundary conditions have to be applied for a converging/diverging nozzle (the flow starts in subsonic regime and becomes supersonic after the nozzle throat)?
Thanks in advance.


Tommy

[TommyM]

I have changed my boundary conditions in the following way:
- Fixed total pressure at inlet

- Fixed total temperature at inlet

[TommyM]

I am sorry.


I have changed my boundary conditions in the following way:
- Fixed total pressure at inlet (totalPressure)
- No impositions on velocity at inlet (pressureInletOutletVelocity)
- Fixed total temperature at inlet (totalTemperature)
- Fixed static pressure at outlet (waveTransmissive)


The simulation seems to work (it is still going on), but I don't know if my boundary conditions are well-posed. Would be better if I change totalTemperature at inlet to static temperature (fixedValue) at inlet?


Tommy