Uçuş Esnasında Değiştirilebilir Kanat Profili Kullanarak NACA 4412’nin Aerodinamik Performansının Artırılması

Abstract

The breakaway of the flow from solid surfaces is defined as stall, which cannot hold onto the surface based on the positive pressure exposure due to geometric or external factors. Flow separation (stall) is the most critical concept affecting the performance of the aircraft. Hence in this study, it is aimed to change the shape of the airfoil profile during the flight to obtain maximum performance at different angle of attack values. 2D computational fluid dynamic analysis is used in this study based on NACA 4412 airfoil profile. In order to achieve higher aerodynamic performance at different angles of attack during flight, two different airfoil profiles were obtained (NACA 4412_1 and NACA 4412_2) by modifying the NACA 4412 airfoil profile and the aerodynamic performances of the original NACA 4412 airfoil profile with the modified airfoil profiles were compared. Analyses were performed between 0° and 23° angle of attack values to carry out the comparison. Drag coefficient, lift coefficient, and flow separation as the performance parameters were investigated. At the end of the study, it was determined that the NACA 4412 airfoil profile angle (α) between 0° and 12°, the NACA 4412_2 airfoil profile angle (α) between 12° and 17°, and the NACA 4412_1 airfoil profile for angle of attack values higher than 17° were suitable for maximum aerodynamic efficiency.