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[ae22b001]

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. 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 working.

 

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 exceeds 3.

Please let me know how to fix this issue.

I will attach pictures

[ae22b001]

Mesh

Solver settings for steady state simulation
I have also tried turning warped face gradient correction off but it still diverges in the transient simualtion.
Courant no - 5
when I start the transient sim, after some iterations:

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

[ae22b001]

Hello, any help would be greatly appreciated. Thanks

 

[ae22b001]

Hi, any ideas on how to solve this problem? It works well with pressure based solver, but does not with the density based solver

[ae22b001]

Hello, any help would be greatly appreciated. thanks 

[ae22b001]

Any ideas? Thanks