Numerical investigation the change of aerodynamic coefficients of NACA 4405 airfoil by installing small analogous airfoil at the top of leading edge

In aerodynamics, flow separation often leads to increased drag and lowering of lift force, which results in instability of the airplane and leads to happen stall. In order to solve this problem, several solutions have been proposed and have been reviewed by aeronautical sciences experts. In this study, a new method is proposed to control theseparation of flow at high angle of attack. The proposed method is that a customizable small analogous airfoil is installed near the edge of the attack and above it to cause a cross interaction between the vortex produced by the small analogous airfoil and the boundary layer on the airfoil and with moving the flow in to the layer the lower boundarylayer leads to controlling the separation phenomenon. Using this method leads to the control of the separation of flow and change of aerodynamic coefficient is controlled at the higher angle of attack and the drag coefficient is prevented from sudden increase. Finally, the aerodynamic performance of the airfoil at large angles is significantly improved

کلیدواژه ها:

aerodynamic coefficients ، flow separation control ، NACA 4405 airfoil ، numerical simulation