How to set inflow mach in a transonic channel?
 

I have a circular arc bump in the middle of the channel. I can only attain M<0.75 at the inlet using Pressure_Inlet and Pressure_Outlet boundary conditions, by reducing exit static pressure. After a normal shock is formed, the inlet Mach does not vary and has the same profile. Is there a work-around? How do I attain inlet Mach of 0.8, 0.85 ,0.9 ???

In transonic tunnels, a converging nozzle is used to attain Mach in the transonic range due to eventual choking at the bump. How do I model it in FLUENT?

Thanks for any help, Johnson

Sorry, I can not have any answers for your problem, but I would like to ask you about my own problem! I have developed a code for the bump problem, but I can't set all the boundary conditions. did you just assume some values for Pback so that P0 can be reached? what are the other boundary conditions? to me it must be P0,T0,flow angle and an extrapolation for inlet and just Pback for outlet, do you know the suitable extrapolation for this problem?