[Alpha_Ashwin007]

Hello all, The inlet of my geometry has a supersonic nozzle. I am trying to simulate flow through it in steady state initially and then later in unsteady conditions.
With the density based solver I was able to get a decent steady state solution altho the residuals weren't perfect(oscillating somewhere between 1e-3 and 1e-4). When I started to run the transient solution , my results start diverging near the wall, which I think is caused by high accept ratio cells near the wall/inflation layers. Without the inflation layers, it is not diverging.

However, when I use the pressure based solver I am able to get really good results with inflation layers as well. I want to recreate the results using density based solver as Mach number in my flow downstream exceeds 3.
Please let me know how to fix this issue.
I will attach pictures

I have also tried turning warped face gradient correction off but it still diverges in the transient simualtion.
Courant no - 5

1.So how do I reduce residuals in steady state, right now its oscialllting somewhere between 1e-3 and 1e-4
2. How do I prevent this from diverging as shown above in transient sim?
Thanks

[Alpha_Ashwin007]

Hello guys, any help would be greatly appreciated, Thanks