可变翼尖角翼片对总阻力降低的影响的计算流体力学研究

Giulia Innocenti, Eric Segalerba, Joel Guerrero
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引用次数: 0

摘要

开发小翼的动机是减少飞机升力引起的阻力。由于小翼是固定装置,其主要局限之一是无法适应多变的飞行条件。为了解决这个问题,本研究提出使用可变翼尖角的小翼,这种小翼可以在不同的飞行条件下进行调整,以优化阻力的减少。在本研究中,我们使用 CFD 仿真器 OpenFOAM 来研究改变小翼翼尖角度的效果。我们没有采用完全网格变形的方法,而是采用了一种准稳定方法,通过将翼尖角从 0º 变为 70º 来研究不同的小翼配置。采用这种方法的主要原因是为了减轻与动态网格划分方法相关的负担。在这种飞行条件下获得的结果表明,就气动效率而言,最佳倾斜角约为 40º。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
Computational Fluid Dynamics Study on the Influence of Variable Cant Angle Winglets on Total Drag Reduction
The development of winglets has been motivated by the need to reduce lift-induced drag in aircraft. One of the main limitations, since they are fixed devices, is related to their inability in adapting to variable flight conditions. To address this issue, this study proposes the use of variable cant angle winglets that can be adjusted to optimize drag reduction under different flight conditions. In this study, we use the CFD solver OpenFOAM to investigate the effects of varying the winglet cant angle. Instead of a fully mesh morphing approach, a quasi-steady approach was taken where different winglet configurations were investigated by changing the cant angle from 0º to 70º. The main reason for taking this approach was to reduce the burden related to the dynamic meshing approach. The results obtained in this flight condition show an optimal cant angle, with respect to the aerodynamic efficiency, around 40º.
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