Flow Behavior analysis over the NACA 4412 airfoil at Different angles of attack

To design and optimize wings, rotor blades and aircraft, it is essential to have a good understanding of the aerodynamic properties of the wing. The aim of this numerical study is to examine and analyze the aerodynamic characteristics of a NACA4412 airfoil at different angles of attack, to capture the lift coefficient, drag coefficient and flow separation. The numerical results provide the variation of air pressure and speed when moving over the airfoil for different angles. We found that increasing the angle of attack increases the lift coefficient. At low angles of attack, the area adheres well to the profile, but beyond 14°, a significant stall occurs in the upper surface flow, forming a large recirculation and turbulence zone, which explains the sudden decrease in the lift coefficient from this angle. This study provides vital information on the aerodynamic performance characteristics of the NACA 4412 airfoil, which may be useful for the design of wind turbine blades, aircraft wings, and drones.