Experiment Name : Flow over a wing with leading-edge rotation.
Analysis Type- External Flow analysis(Time Dependent Analysis)
Airfoil- NACA0024 (0.2m chord,0.6m span),
Leading-Edge Cylinder- 25mm dia,rotating at 400rad/s , 3820RPM clockwise.
When i started the simulation mesh generation finished properly no prb faced.
But after some iterations "High Mach Number Flow Exists" was shown in solver..ALSO the PRESSURE n VELOCITY plot was totally green no changes there..
I have attached the main files. Plz take a look.