[AKdfc]

Hi all,

I am trying to simulate a supersonic flow in a straight duct using ANSYS Fluent with the objective to produce a normal shock as the simulation output and compare the same against normal shock analytical solution.

The flow is assumed to be steady, inviscid and adiabatic.

The boundary condition being imposed at the inlet is a pressure inlet BC with the specification of Total and static pressure values and a pressure outlet BC at the outlet.

I am having trouble firstly initializing the flowfield with a supersonic flow and if it happens so (Standard initialization), the flowfield becomes fully supersonic after a certain number of iterations.

Could anyone suggest what I am missing in the solution setup?