摘要
翼尖涡是客机尾涡的重要组成部分,不仅会产生诱导阻力影响飞机的经济性,同时还会带来尾迹遭遇问题进而影响到后续飞机的安全性。随着数值模拟和实验技术的提升,对翼尖涡结构特征、动力学特征、不稳定性发展、演变规律等现象和机理的认知不断加深,并取得了丰富的研究成果。近些年,随着不稳定性理论和模态解析方法的发展,研究者针对翼尖涡的不稳定性及其模态特征开展研究,试图揭示翼尖涡不稳定性演变的规律及机制,并期望能建立一种基于不稳定性的流动策略,从而实现对翼尖涡失稳衰减的最优化控制。本文对飞机翼尖涡不稳定性及其模态特征的研究展开综述,首先介绍翼尖涡的不稳定性特征,然后比较典型模态分析方法的基本原理,进而分析翼尖涡不稳定性及其模态结构特征,最后讨论翼尖涡不稳定性模态分析的研究现状及未来发展趋势。
Wingtip vortex is an important part of the civil aircraft wake vortex,which not only induces drag and affects the economy of the aircraft,but also causes the wake encounter problem and affects the safety of the follow-up aircraft.With the advancement in numerical simulation and experimental measurement techniques,the understanding of the wingtip vortex structure characteristics,dynamic characteristics,instability development,evolution and other phenomena and mechanisms have been deepened,and various research results have been obtained.In recent years,with the development of instability theory and modal analysis methods,researchers have studied the instability and modal characteristics of wingtip vortices,trying to reveal the law and mechanism of the instability evolution,with the hope to establish a flow control strategy based on instability to achieve the optimal control to accelerate the attenuation and dissipation of wingtip vortices.This study reviews the research on wingtip vortex instability and its modal characteristics.We firstly introduce the instability characteristics of wingtip vortices,then compare the basic principle of typical modal analysis methods,and then analyze the wingtip vortex instability and its modal structure characteristics.Finally,the research status and future development trend of wingtip vortex instability modal analysis are discussed.
作者
向阳
吴奕铭
陈炫羽
程泽鹏
刘洪
XIANG Yang;WU Yiming;CHEN Xuanyu;CHENG Zepeng;LIU Hong(School of Aeronautics and Astronautics,Shanghai Jiao Tong University,Shanghai 200240,China;Wu Zhenyuan Aerodynamics Center,Shanghai Jiao Tong University,Shanghai 200240,China;School of Aeronautic Science and Engineering,Beihang University,Beijing 100191,China)
出处
《空气动力学学报》
北大核心
2025年第1期62-94,I0002,共34页
Acta Aerodynamica Sinica
基金
国家自然科学基金(12202273,91952302)。
关键词
大型客机
翼尖涡
模态分解
涡不稳定性
流动控制
large civil aircraft
wingtip vortex
modal decomposition
vortex instability
flow control
