Technology development and various needs to help humans work without increasing the risk of human safety. One of these technologies is the Unmanned Aerial Vehicle (UAV), commonly referred to as a drone. UAV technology is required in various sectors, both civilian and military. Therefore, research was conducted on the use of winglet variations on the NACA 4415 airfoil to predict aerodynamic performance and to find the best option for winglet geometry on the NACA 4415 airfoil with a wingspan specification of 1100 mm, root chord of 330 mm, and tip chord of 188,5 mm. The research was conducted using the CFD method at a cruising speed of 33,33 m/s and air density of 1,16681 kg/m3. There are six variations of winglets in this study: no winglets, fence wingtips, raked wingtips, canted winglets, blended winglets, and split winglets. The results indicate that a wing with a winglet can increase the lift-to-drag ratio (L/D) by approximately 3% to 6% at an angle of attack (AoA) of 0° to 12°. The value of L/D depends on different angles of attack and winglet variations.
Numerical Study of Winglet Variations on Aerodynamic Performance of NACA 4415 UAV Airfoil
Advances in Engineering res
International Conference on Science and Technology ; 2024 ; Yogyakarta, Indonesia October 23, 2024 - October 24, 2024
Proceedings of the 10th International Conference on Science and Technology (ICST 2024) ; Kapitel : 22 ; 237-246
01.07.2025
10 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
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