Hi, I am new using CFD... I'm using flow simulation solidworks, I got a problem trying to simulate the supersonic first stage of an axial flow compressor (rotor only).
This are my calculation of free vortex DCA blade:
Gas | Air | ideal |
P1 | 101.325 | Kpa |
T1 | 288 | K |
T2-T1 | 5.50467833 | K |
T2 | 293.504678 | K |
P2 | 107.438473 | Kpa |
N | 377 | RPM |
FLOW | 397 | Sm3/s |
I don't know why the iterations of the pressure go so high and never converge... I let you some print-screens to let figure out what's going on.
I will appreciate any help, comment or correction of whatever mistake that I have done.
SolidworksFlow Simulation