[Nitrox416]

Hi all,
I'm studying for a college project a large compressor fan the mach is around 0.23 at inlet and 0.217 at outlet. I've decide to begin the study with incompressible case due to only little variation in temperature and so density during compression (around 20°), and then make the compressible case for further refinement.
-the moving cascade has been achieved imposing 0 motion to the walls in absolute frame and moving the fluid cell with the right velocity
The compressi
-boundary condition are:
-velocity inlet with specified velocity
-pressure outlet, 11375 Pa
-periodic boundary where needed
Now if I consider an operating pressure of 91000 Pa why the static pressure at inlet do not respect this and report me a 98000 Pa static pressure?
Fluent is telling me that the only solution to my problem with this condition is to have an higher initial pressure.?

2) in the compressible case I have same case I constantly experience supersonic flow with velocity inlet BC.
With Pressure inlet and 0 gauge pressure the flow is reversing constantly, as said before do you think that the problem is wrong from data and not from design? or I should check something else?
Thanks for help