[Mary P]

I am carrying out an analysis for hypersonic flow around a re-entry capsule with an air jet impinging into the free stream which is to act as a drag reduction system. Temperature and pressure inputs correspond to those present at 42km altitude. (T= 255.9k, P=220 Pa, Density = 0.0030kg/m3)

The first set of analysis were carried out to obtain flow parameters without the opposing air-jet. The solution converged for the given conditions stated below and a proper bow-shock pattern was obtained as well but the parameters across the shock didn't seem to follow the conventional results. Total temperature across the bow shock shows a dip whereas across the shock it should remain constant ( if I'm not wrong). Other downstream parameters too are incorrect.

It'll be really helpful if someone looks into this and guides me with further analysis.

The general solver and model settings being used are:
1.Parallel solver with double precision.
2. Energy model - ON
3. k-ε model( Realizable) with enhanced wall treatment.
4. Flux model is AUSM
5.Explicit scheme.
6.Flow order is 1st order upwind.

P.S: It's a 2D analysis. Mach no: 6