NACA 2412 Airfoil

Objective: Objectives To simulate and analyse flow over NACA 2412 Airfoil and calculate drag and lift coefficients for different angle of attack as follows. Angle of attack = 1º Angle of attack = 5º Angle of attack = 10º Angle of attack = 15º also to simulate for different Turbulence model k-ω -sst RNG -k-ϵ…