Analisis Karakteristik Aerodinamika Penambahan Winglet Tipe Canted pada NACA 2412 dengan Menggunakan Ansys 2025 R1

Abstract

A winglet is an aerodynamic device positioned at the wingtip, functioning to reduce wingtip vortices that contribute to induced drag, thereby enhancing the overall aerodynamic efficiency of an aircraft. This study investigates the aerodynamic characteristics of a wing equipped with canted winglets based on the NACA 2412 airfoil using ANSYS 2025 R1 computational simulations. The wing model utilized in this research adopts the NACA 2412 airfoil, which is implemented on the Indonesian Air Force’s Cessna 172 aircraft. Canted winglet configurations were analyzed at cant angles of 15°, 30°, and 45°, with simulations conducted at a cruise velocity of 167 km/h (46 m/s) under angles of attack of 2°, 4°, 6°, and 8°. The simulation results indicate that, at a velocity of 46 m/s, the wing without a winglet demonstrates superior aerodynamic efficiency compared to wings equipped with canted winglets, particularly at higher angles of attack. This is evidenced by a higher lift-to-drag (L/D) ratio for the baseline configuration. Therefore, it can be concluded that the addition of canted winglets does not significantly improve aerodynamic efficiency under the tested flight conditions.