Problem with supersonic flow
 

Hello together,

i´ve got a problem with the Fluent solver that don`t converg. I´am simulating a radial turbine blade and want to show the pressure field with the shock waves.

I tried the following:

- different mesh to exclude that the error is caused by the mesh
- reduced courant number (0.1 ; 0.01 etc.)
- solution steering with supersonic flow in the "run calculation" settings
- velocity inlet instead of pressure far field in the boundary conditions
- w-cycle, v-cycle, F-cycle in the "advanced solution controls"

I always used the density based solver. Inviscid and energy equation is enabled.

Does anyone have an idea of how I can make the solver converge?

Kind regards

Does no one have an Idea?

What are the boundary conditions that you specify? How is your domain shaped?

Also, but this is just my curiosity, why have you chosen euler solver?

Rob

I used the euler equation after I have used the k-epsilon. I just wanted to simplifie the problem as a test because the solver didn't converge with turbulence model.

I mesh the geometrie with triangle or submap in Gambit.

Boundaries are:

INLET (pressure far field)
- Mach 1.9
- 140000 Pa absolute

OUTLET (pressure outlet)
- 20000 Pa absolut

After 3 days of try and fail I got greate improvements with the hybrid initialization (first I always tried standard initialization)

Why do you initialize the inlet as a pressure far field? I would try with pressure inlet.
Instead of using the hybrid initialization try to initialize the problem using fmg initialization (in the Fluent console you can find it under 'solve/initialize/FMG initialization').

Hope it helps,

Rob

Dear Rob,

thanks a lot for your reply. I´ll try out your suggestions.

Concerning pressure far field:

I found a tutorial in wich they used the pressure far field. So that´s why I used it too :)

Pretty curious, but it depends also on how is geometrically designed your domain.
Let me know if it works, normally FMG initialization solved many of my divergence problems.