Flow simulation over NACA airfoil

Objective: Flow Simulation over a NACA airfoil is carried out at a velocity of 600m/s in x-direction, for different angle of attack, viz. 0,2,4,6,8 and 10. In the following model, only 0 degree angle of attack is shown(but for results it was changed over and over again). https://drive.google.com/file/d/11rI_5kAaZtmLemt56M0zAcReNxOLuJ8w/view?usp=sharing…