[mahbood]

Hello,

I am working on modeling of internal Supersonic flow. with B.C. of Pressure Inflow or Mass flux, and Pressure Outflow. I put everything according my Total (Stagnation) pressure, Temperature. working fluid as Air, (Density: Ideal Gas Model). trying to solve with Pressure based solver, SST, or Density Based Solver, SST.
The initial values of intake speed and Static T and P, in reference Boundary condition, are correct based on Mach number. But Apparently, A normal Shock is happening just at the flow intake (where it should not happen). so, flow turns to be subsonic. I checked the results. velocity and pressure was equal to after shock values. but I don't know what should I do to prevent this intake shock wave.

I would appreciate if anybody can help me with this matter.