Analysis of The Effect of Winglet Angle Variation (Cant) and Sinusoidal Wing Profile on The Efficiency of Uav Unggeh Tabang Afrg-019

Editia, Muhammad Akbar (2025) Analysis of The Effect of Winglet Angle Variation (Cant) and Sinusoidal Wing Profile on The Efficiency of Uav Unggeh Tabang Afrg-019. S1 thesis, Universitas Andalas.

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Abstract

Unmanned Aerial Vehicles (UAV) or unmanned aircraft have increased significantly in various sectors, including military, surveillance, mapping, and agriculture. One of the main challenges in operating UAVs, especially fixed-wing UAVs, is Aerodynamic efficiency. Aerodynamic efficiency is critical because it directly impacts the Performance of UAVs like cruising range, flight duration, and operational costs of the UAV. Therefore, various efforts have been made to improve aircraft aerodynamics, one of which is through wing and winglet design. This study investigates the effect of varying winglet Cant angles and sinusoidal leading-edge profiles on UAV performance. The simulations are carried out using Ansys Fluent with three angles of attack: 5˚, 15˚, and 30˚. The winglet Cant angle variations include 15˚, 45˚, and 75˚. For the sinusoidal leading-edge profile, three UAV configurations are analyzed: the baseline UAV, UAV A with an amplitude of A = 0.03 × chord and a wavelength of λ = 0.5 × chord, and UAV B with an amplitude of A = 0.05 × chord and a wavelength of λ = 0.5 × chord. The chord length is 215 mm for the wing and 125 mm for the winglet. The objective is to observe changes in the lift and drag coefficients in response to these variations. The results of the aerodynamic simulation aim to show how changes in winglet angles and sinusoidal leading-edge profiles affect the aerodynamic performance of UAVs. This performance is evaluated using the lift coefficient, drag coefficient, and lift-to-drag ratio. This study is expected to provide a better understanding of how these design variations can influence future UAV development. Based on the research results, it was found that the sinusoidal wing profile can increase the lift coefficient at high angles of attack (AoA), with the highest value observed for the Sinusoidal B profile, achieving a maximum CL of 0.58997595. In terms of overall aerodynamic performance, as indicated by the CL / CD ratio, the optimal winglet configuration was found to be at a cant angle of 15˚. Furthermore, for high-angle-of-attack conditions, the best overall configuration was the UAV B with a 15˚ cant angle.

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