[Abhinand]

Hello CFD giants,
I am simulating a supersonic flow over a flat plate with an injector in a viscous laminar model. I have a converged solution with the first order scheme, but I want to get a better solution using a second order upwind scheme. I had previously used a courant number of 0.96, density based solver settings with AUSM Implicit scheme.

But now when I continue my calculation and change to second order scheme, the residuals shoot up drastically. How do I control that and achieve a second order converged solution.

Any help and advice is appreciated.
Thanks for your time guys.