Initializing the pressure in a region
I am trying to initialize the static pressure in a specific mesh region (fluid zone) to approximately Mars ambient pressure. I am trying to determine the plume structure exiting a supersonic nozzle-the rocket exhaust gases accelerate to Mach 4.5 at the exit.
I have set the operating pressure to the desired value, but I am not getting the shock structure I should. I have set up my problem where I have coupled implicit, axisymmetric flow, inviscid. I have only pressure boundaries-outlet and inlet. I am using an ideal gas.
If you could provide some assistance-it would be great. thanks. -manish
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