Design Optimization of Wingtip Devices to Reduce Induced Drag on Fixed-Wings

摘要

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.