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Issue with specifying boundary conditions for supersonic retropropulsion |
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September 25, 2020, 02:29 |
Issue with specifying boundary conditions for supersonic retropropulsion
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dinesh Choudhary
Join Date: May 2020
Posts: 2
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Hello,
I am simulating a supersonic bow shock on air jet from nozzle inlet thrusting into the oncoming supersonic freestream with rhoCentralFoam k-ω SST model. The problem is while running the case simulation crashes at very early stage, i suspect that my boundary condition are incorrect specifically the supersonic freestream boundary conditions. My setup for p, T and U are as below. p: Code:
internalField uniform 9831120; boundaryField { inlet { type totalPressure; value uniform 9831120; p0 uniform 9831120; psi thermo:psi; gamma 1.4; } freestream { type waveTransmissive; value uniform 13800; field p; psi thermo:psi; lInf 0.43815; fieldInf 13800; gamma 1.4; } walls { type zeroGradient; } axis { type empty; } wedge1 {type wedge;} wedge2 {type wedge;} } Code:
internalField uniform 294; boundaryField { inlet { type totalTemperature; value uniform 294; T0 uniform 294; psi thermo:psi; gamma 1.4; } freestream { type zeroGradient; } walls { type zeroGradient; } ... Code:
internalField uniform (-694.404 0 0); boundaryField { inlet { type zeroGradient; } freestream { type fixedValue; value uniform (-694.404 0 0); } walls { type noSlip; } ... can anyone please help me out to set proper boundary condition. |
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