Obtaining the lift force and drag force of a NACA0017 airfoil of 100 mm chord in supersonic flow of the order Mach 3 and finding the critical angle of attack when M>3.0

Objective: Obtaining the lift force and drag force of a NACA0017 airfoil of 100 mm chord in supersonic flow of the order Mach 3 and finding the critical angle of attack when M<0.3 I have chosen a NACA0017 airfoil with a chord length of 100mm. The type of analysis is an external flow analysis with air as the medium.…