Analisis Perbandingan Karakteristik Aerodinamika Split-Tip Winglet dan Sharklet pada Sayap NACA 653-218 Menggunakan Digital Subsonic Wind Tunnel
DOI:
https://doi.org/10.54706/senastindo.v7.2025.428Keywords:
Airfoil, winglet, Split-TipAbstract
This study aims to analyze and compare the lift force, drag force, and lift and drag coefficients of a NACA 653-218 airfoil wing equipped with different wingtip configurations: split-tip winglet, sharklet, and no winglet. The experiment was conducted using a Digital Subsonic Wind Tunnel with airflow velocities of 5 m/s, 15 m/s, and 25 m/s, and Angle Of Attack variations from 0° up to stall, with 2° intervals. The test specimen was designed based on the NACA 653-218 wing with an interchangeable tip to accommodate each winglet configuration. The results show that the addition of a sharklet produced the highest lift compared to the other configurations. At a velocity of 25 m/s and an Angle Of Attack of 20°, the wing without a winglet generated a lift of 1.25 N, with a split-tip winglet 1.36 N, and with a sharklet 1.39 N. These findings indicate that adding a sharklet to the NACA 653-218 wing improves aerodynamic efficiency by providing higher lift performance compared to both the split-tip winglet and the baseline wing
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