I am trying to run a shocked flow case in an 1D-Euler code with subsonic inlet and outlet. The solver of the flow equations is a MUSCL Flux vector splitting. However, the code does not converge. Is there an extra boundary condition on the wave?

I'm not sure what bc's you are applying, but for a subsonic inlet and subsonic outlet you need to specify 2 characteristics at the inlet and 1 characteristic at the outlet, so for your 1D problem I would specify stagnation pressure and stagnation temperature at the inlet and static pressure at the outlet.

I'm not sure what you mean by running a 'shocked flow case' though - you can get a normal shock forming but this is dependent upon your geometry ( do you have a convergent or a convergent-divergent nozzle perhaps ? ) and pressure ratio ( which you are specifying by prescribing P0 upstream and Pstatic downstream ).

Does this help ?, Simon.

These are the bc's I am using. The geometry is a convergent-divergent nozzle. I am specifying the pressure ratio by giving as an input the isentropic Mach number.

have you validated the method for purely subsonic flow? set the exit pressure to just below the total pressure and see if you can get the isentropic subsonic solution. then you can move on to higher Mach numbers (lower exit pressure).

hi mani im a learner in compressible fluid flow, can u send me any tutorial regarding the compressible fluid flow in a nozzle. waiting for your reply.