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[ravitejagonnabathula007]

Dear CFD buddies,


I'm simulating a supersonic inlet by increasing the back pressure ratio. Till the the back pressure ratio of 4 at the interval of 1 I was able to generate results. When I'm simulating for back pressure ratio of 5 I couldn't solve and AMG solver is being detected.

Tried refining the mesh- didn't worked

Settings:
altitude30km (corresponding P, T values)
Mach :2.18
Desnity based solver
Spalart–Allmaras turbulence model
Explicit solver
courant number -0.5

Hope I could find the solution.
All suggestions are accepted

[Keyur Kanade]

With Mach 2.18, you can use pressure based solver. 

Use ideal law for density. 

Please try refined hex or tet with prisms mesh. 

Check mesh quality. Is it 2D or 3D?

Regards,

Keyur

 

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[ravitejagonnabathula007]

its is 2D. ill try with pressure based solver and update the status

[ravitejagonnabathula007]

I tried solving with pressure based solver, but it diverged nearly at 1000 iterations.

can u give me some more suggestions to proceed further?

[Rob]

Check mesh resolution around the shock: chances are the pressure gradients are high and you need to refine the mesh. 

[Keyur Kanade]

Please check by refining the mesh. 
Also please check mesh quality. 

With student version you have limit of 512K cells. 

So you may need to consider to reduce problem size as well. You may check symmetry in the model. 

Regards,

Keyur

 

If this helps, please mark this post as 'Is Solution' to help others.

Guidelines on the Student Community

How to access ANSYS help links