TY - GEN
T1 - Design Optimization of Wingtip Devices to Reduce Induced Drag on Fixed-Wings
AU - Makgantai, Boitumelo
AU - Subaschandar, N.
AU - Jamisola, Rodrigo S.
N1 - Funding Information:
The authors would like to acknowledge the funding support on this work from the Botswana International University of Science and Technology (BIUST) Drones Project with project number P00015.
Publisher Copyright:
© 2021 IEEE.
PY - 2021/6/15
Y1 - 2021/6/15
N2 - The current study investigates drone wing parameter optimization based on aerodynamic performance, lift-to-drag ratio (L/D), and endurance. Optimized aircraft have better performance, i.e., more range, good payload capabilities, and higher maneuverability. Wingtip devices for large aircraft flying at subsonic speeds at high Reynolds number have been extensively analyzed. In this study, we analyse the performance differences of these wingtip devices on Unmanned Aerial Vehicles (UAVs) due to the fact that they operate at very low speeds and high Reynolds numbers. Computational Fluid Dynamics (CFD) analysis was conducted for both aircraft and drone wings. The first set of simulations performed was for an aircraft swept-back wing. It was designed using sections of a two-dimensional aerofoil NACA 0015. Another set of simulations was for a drone moderate-tapered-wing design using sections of NACA632615 aerofoils. The analysis was carried on three wingtip devices: blended winglets, drooped wingtip, and spiroid winglets. The results were compared and analysed between the performance of these winglets on an aircraft wing and a UAV wing.
AB - The current study investigates drone wing parameter optimization based on aerodynamic performance, lift-to-drag ratio (L/D), and endurance. Optimized aircraft have better performance, i.e., more range, good payload capabilities, and higher maneuverability. Wingtip devices for large aircraft flying at subsonic speeds at high Reynolds number have been extensively analyzed. In this study, we analyse the performance differences of these wingtip devices on Unmanned Aerial Vehicles (UAVs) due to the fact that they operate at very low speeds and high Reynolds numbers. Computational Fluid Dynamics (CFD) analysis was conducted for both aircraft and drone wings. The first set of simulations performed was for an aircraft swept-back wing. It was designed using sections of a two-dimensional aerofoil NACA 0015. Another set of simulations was for a drone moderate-tapered-wing design using sections of NACA632615 aerofoils. The analysis was carried on three wingtip devices: blended winglets, drooped wingtip, and spiroid winglets. The results were compared and analysed between the performance of these winglets on an aircraft wing and a UAV wing.
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U2 - 10.1109/ICUAS51884.2021.9476801
DO - 10.1109/ICUAS51884.2021.9476801
M3 - Conference contribution
AN - SCOPUS:85111458200
T3 - 2021 International Conference on Unmanned Aircraft Systems, ICUAS 2021
SP - 1459
EP - 1465
BT - 2021 International Conference on Unmanned Aircraft Systems, ICUAS 2021
PB - Institute of Electrical and Electronics Engineers Inc.
T2 - 2021 International Conference on Unmanned Aircraft Systems, ICUAS 2021
Y2 - 15 June 2021 through 18 June 2021
ER -