Analisis Karakteristik Aerodinamika Penambahan Spiroid Winglet Pada Naca 23015 Dengan Metode Computational Fluid Dynamic

Abstract

Improving aerodynamic efficiency is a primary focus in the aviation industry to reduce fuel consumption. One of the main causes of inefficiency is induced drag formed at the wingtips. The use of winglets has proven effective in addressing this issue, and the spiroid winglet is one design development that promises superior performance. This study aims to analyze and compare the aerodynamic characteristics, including the lift coefficient (CL), drag coefficient (CD), and lift-to-drag ratio (L/D), between a wing with a standard NACA 23015 airfoil and one modified with the addition of a spiroid winglet. The analysis was conducted using Computational Fluid Dynamics (CFD) numerical simulations with ANSYS 2025 R1 software. Simulations were performed on a three-dimensional wing model with varying angles of attack (AoA) of 0°, 2°, 4°, and 6° under airflow conditions of 230 m/s. Simulation results show that the addition of spiroid winglets has a significant impact. The configuration with spiroid winglets produces a consistently lower drag coefficient (CD) compared to the standard configuration, especially at high angles of attack. The most significant improvement is seen in the maximum L/D ratio. Flow visualization also confirms that the spiroid winglets are effective in dispersing and weakening the wingtip vortex. It is concluded that the implementation of spiroid winglets on the NACA 23015 airfoil successfully improves the overall aerodynamic efficiency, primarily through the reduction of induced drag, which leads to an improvement in the L/D ratio.