I am in a dire situation cuz my project will be cancelled if i can't solve this within a few days. So I seek your help with this.. Whole details about the project is given below,
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.
Problem Details- i faced no problem regarding the setup. everything's ok tho i have sm questions about total analysis time and output step time.
I put 20s and 5s values for these options.
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 blue no changes there..
I have attached the main files. plz run those files in ur pc n lemme knw if there's anything wrong with my setup..please save me i tried changing every values that i know of but it just wont b solved..plz help me.