Flow simulation over a NACA0017 airfoil for different values of angle of attacks by using SolidWorks.

Objective: AIM: 1) Model the flow over a NACA0017 airfoil For the angle of attacks 0,2,4,6,8,10. 2) compare the lift and drag forces for each cases. INPUTS: Velocity of Air: 500m/s CASES: 1) Angle of Attack = 0 deg Pressure Plot: Velocity Plot: Table: Explaination: From the velocity & Pressure cut plot, Air stream…