Fluid Mechanics and Heat Transfer (Flow Around an Airfoil)

need someone to make a project Flow Around an Airfoil 1. You must investigate the effects of compressibility and shock wave generation over the specific NACA airfoil with Ansys Fluent at various velocities. Subsonic, Transonic, and Supersonic conditions must be considered. These conditions may differ depending on your airfoil. Effects of viscous drag will be neglected for ease of calculation (inviscid). Critical Mach Number (by increasing the velocity) and Zero Lift angle (by increasing the attack angle) must be found. 2. Use a NACA 4 Digit generator ([login to view URL] or another one you like) 3. NACA 2421 example is shown below. You must use your student IDs 1st, 2nd, 3rd, and last digits with the given order. Example ID # 227517629 > 2, 70, 29 >NACA 2729 For more info, I uploaded the project file