CFD approach to analyze the aerodynamics potentiality of rotary leading edge aircraft wing at different angle of attack

Aerodynamics of the rotary leading edge aircraft wing was experimented by the help of modified NACA-0010 airfoil. CFD simulation was done by converting the 2-D NACA-0010 airfoil to a 3-D aircraft wing. A cylinder was mounted at the leading edge of the modified aircraft wing and then it was allowed to rotate in anti-clockwise direction at a certain rpm. The simulation showed that there was a significant improvement of lift generation in modified wing. Parametric approach showed that at zero degree angle of attack when a symmetric airfoil typically doesn't generate any lift at all but due to the effect of rotary cylinder positioned at the leading edge of modified aircraft wing there was a finite amount of lift generation. The simulation was done for this modified aircraft wing model at different angle of attack keeping the rpm of leading edge cylinder constant and in all cases significant improvement of lift generation was noticed. The results were further verified by applying a change in rpm also for a series of angle of attack and the aerodynamic performance has been analysed.