[Xazopaido]

Hey Guys!

First of, I would like to say congats to your site! Very helpful and keep up the excellent work!

So, I have basically designed a transonic compressor stage. A row of rotor and a row of stator. I have already have the 3D model and created the mesh and now I am stack in the setup section of Fluent.
I would like to model a compressible flow going into the compressor stage. THe result I want to get is an increase in pressure in the stator outlet. I should menthion that I used the mixing plane function of fluent and my model is ready for simulation. I run some simulations using pressure based solver with the air dencity constant and I got pretty good results (in my opinion) (I mean that I got the pressure rise I want and the temperature rise that I want).

The thing is when I change the density from constant to ideal gas I get
messages like Divergence in AMG solver and float point exception! And the simulation stops. I would like to use compressible flow because that would give me more realizable results. And also with compressible flow I can see Mach number contours in the rotor tip which I am intersted in as well.

What do you think it is the problem? Sorry for the looooooooong post!! I'd really appreciate any help! Thanx in advance!