Flow simulation of a NACA2412 airfoil at various angles of attack

Objective: The flow over a NACA2412 airfoil is performed at various angles of attack and the lift and drag properties are studied at those airfoils. The angles of attack being 1, 5, 10 and 15 degrees. Airfoils are generally not studied for a 0 degree case since there would be zero lift for a symmetric airfoil. This can be explained…