Hi
I am trying to simulate the motive nozzle in ejector which is simply converge diverge nozzle. The flow inside this nozzle is the carbon dioxide. At inlet the flow start as incompressible flow then it transfer to sonic in the throat section then converted into supersonic at the exit. The inlet BC of the refrigerant are: the pressure 40[psi] and the temperature 35C and the outlet BC is the pressure 30[psi]. I have used The High Mach Number Turbulent Flow, Spalart-Allmaras model. My demand is to increase the inlet pressure to higher range (8-12Mpa).
I am very keen for help became I am using a trial version of the COMSOL 5.1 with very short ending period.
Mohammed
I am trying to simulate the motive nozzle in ejector which is simply converge diverge nozzle. The flow inside this nozzle is the carbon dioxide. At inlet the flow start as incompressible flow then it transfer to sonic in the throat section then converted into supersonic at the exit. The inlet BC of the refrigerant are: the pressure 40[psi] and the temperature 35C and the outlet BC is the pressure 30[psi]. I have used The High Mach Number Turbulent Flow, Spalart-Allmaras model. My demand is to increase the inlet pressure to higher range (8-12Mpa).
I am very keen for help became I am using a trial version of the COMSOL 5.1 with very short ending period.
Mohammed