The study the angle of attack and lift magnitude of a wing using COMSOL software

Abstract

Angle of attack (A.O.A.) is defined as the angle at which the chord of an aircrafts wing meets the relative wind. At low angles of attack, the wing could just create a small amount of lift, and it also experience a small amount of drag. As the A.O.A. increases, both lift and drag will increase. However, when the wing reaches a critical angle of attack, the lift it could produce will quickly decrease, since the separation of the air flow and the wing surface. The objective of this study is to find the relationship between the angle of attack and the lift coefficient(which is proportional to the lift it could produce) of the wing. And as a conclusion, we find that the A.O.A. increase, the lift coefficient will also increase, and if the inlet velocity, the wings surface area and the velocity remains constant, when the lift coefficient increase, the lift will also increase.