在风洞中对无人驾驶飞行器（UAV）的翼尖装置进行计算分析和验证

Proceeding Series of the Brazilian Society of Computational and Applied Mathematics Pub Date : 2023-12-18 DOI:10.5540/03.2023.010.01.0032

Diego Osorio, Emilio Insfran, Ms. Ing. J. de Egea, Ing. C. Meaurio

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引用次数: 0

摘要

摘要 .无人机系统在民用和军用航空市场的应用促使人们开发可提高此类飞机性能的方案。本文旨在通过 CFD 软件 Tdyn 和风洞试验验证，分析有翼尖装置（小翼）和无翼尖装置（小翼）无人机机翼的气动行为。在最大 Cl/Cd 比的特定攻角下，比较了无小翼机翼与带不同曲率小翼机翼的升力（Cl）和阻力（Cd）系数。结果表明，与翼尖不带任何其他类型装置的机翼相比，带小翼的机翼可将 Cl/Cd 系数提高 4.5%。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

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Computational analysis and validation in wind tunnel of wing-tip devices for unmanned aerial vehicle (UAV)

Summary . The application of UAV systems within the civil and military aeronautical market encouraged the development of options that increase the performance of this type of aircraft. This paper´s objective is to analyze the aerodynamic behavior of a wing with and without wingtip devices (winglets) for a UAV, through the CFD software Tdyn and wind tunnel tests validation. The lift (Cl) and drag (Cd) coefficients of the wing without winglets were compared to the wing with different curvature winglets at specific angles of attack for maximum Cl/Cd ratio. The results showed that the wing with a winglet can offer an improvement in the Cl/Cd coefficient of 4.5% compared to the wing without any other type of device on the wingtip.

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Proceeding Series of the Brazilian Society of Computational and Applied Mathematics

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