Air Flow over NACA0017

Objective: In this project I stimulated an air flow simulation over a NACA0017 airfoil with attack angles 0, 2, 4, 6, 8 and 10 to compare the lift and drag forces generated in these cases. A mesh refinement of 3 is used on the surface of the airfoil over which a flow of 600 m/s passes. The flow through time in all the simulations…