Supersonic Intake , Pressure Outlet Boundary Condition.

Hello I have a problem about outlet boundary conditions .  I have C-D type Supersonic Air Inlet I try to solve back pressure ratio. My setup options are Operation Condition 0 , Pressure inlet : Total Gauge Pressure 300000Kpa Supersonic/initial 54660 Pa which is equal to M = 2.0 the inlet has a Normal Shock wave at throat then it will diffuse. Outlet condition is 247676 Pa.  Problem is when the flow pass the throat the flow is increasing mach number also end of the simulations ? cross out the total pressure contours Flow doesnt reach outlet conditions. 

Pic about boundary conditions .boundary conditions.

Same Problem.

https://www.researchgate.net/post/How_to_assign_a_Back_pressure_in_supersonic_flow_conditions

 

 

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