I have already done a post on supersonic flow over 23 degree wedge. In that post, we were intentionally creating a situation where the shock wave would be detached from the obstacle. The set-up in that case is certainly appropriate when the shock is attached as well. However it is possible to use an even simpler set up for an attached oblique shock.
In this post I go over the numerical solution to the compressible boundary layer equations. This is very useful when a quick estimate of shear stress, wall heat flux, or boundary layer height if necessary.
In this post I will go over the set up and solution of a pressure driven nozzle flow with a shock located in the diverging section. This refers to the type of flow problem described by region b in my page covering stationary normal shock-waves.
In this post I will simulate inviscid Mach 1.5 flow over a 23 degree wedge of a finite height. Continue reading Mach 1.5 flow over 23 degree wedge – rhoCentralFoam