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:
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.