Analisis Penggunaan Winglet Pada Pesawat Udara Cessna 150 Dengan Profil NACA 2412

Abstract

The Cessna 150 is a light aircraft that is widely used in the world of general aviation. One important aspect in designing an aircraft, including the Cessna 150, is the wing design. When there is a meeting of air flows with different pressures from the top and bottom of the aircraft wing, it can cause a vortex to form at each wing tip. The impact of this vortex is that drag force increases, lift force and fuel efficiency decrease and turbulence can occur. One modification to aircraft wings to reduce the impact of these vortices is the use of winglets. This has been widely applied to the latest commercial aircraft to increase aircraft efficiency. The aim of this research is to analyze the use of winglets on a Cessna 150 aircraft with a NACA 2412 profile. This research uses Xflr5 numerical simulation with a 3D geometric configuration. The winglet shape used is cant angle with bend angles of 0°, 15, 30°, 60°, and 90° which were tested at angles of attack of 0°, 3°, 6°, 9°, 12°, 15°, and 18° with an air speed of 46 m/s. The research results show that the NACA 2412 airfoil with winglets is able to increase wing performance efficiency. This is proven by the visualization of air flow in modifications with winglets which can reduce vortices so that the air flow becomes smoother/laminer. In addition, numerical studies show an increase in the value of the lift coefficient (C_L),  a decrease in the value of the drag coefficient (C_D),  , and a better /  ratio (C_L/C_D) with the use of winglets, where the winglet efficiency is best at a cant angle with a bend angle of 30°.