fluent6 unable for transsonic, compressible flow ?

Tobias

Hello, I'm trying to simulate a highspeed transsonic (fluid domain including areas with with local Mach Number greater and areas with local Mach Number lower than speed of sound) air compressor. Until now fluent was not able to reach convergence and altough not able to reach continuity of massflow in and out. Anybody who knows something that could help, please write your ideas down or contact me via email: tfroebel@gmx.de. Thank you and please excuse my bad english skills.

Here is some data to specify my simulation:

grid: 1,2 mio cells Solver Fluent6 3d, coupled,explicit Boundaries: rotor: total pressure inlet->mixing plane between rotor an stator-> stator: static pressue outlet mixing plane: conserve total enthalpy Fluid: air, normal conditions, 288.15K, 101325 Pa turbulence model: SST k-w initial guess: possible average values between inlet and outlet