飞机尾涡系Rayleigh-Ludwieg不稳定性实验研究

doi:10.7527/S1000-6893.2015.0091

流体力学与飞行力学

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飞机尾涡系Rayleigh-Ludwieg不稳定性实验研究

鲍锋¹, 刘锦生¹, 朱睿¹, 刘玥²

1. 厦门大学物理与机电工程学院, 厦门 361005;
2. 华侨大学厦门工学院, 厦门 361021

收稿日期:2015-01-27 修回日期:2015-03-30 出版日期:2015-07-15 发布日期:2015-04-01
通讯作者: 鲍锋男, 博士, 教授。主要研究方向: 实验流体力学, 水洞设计, 航空推进, 流动控制。 Tel: 0592-2184789 E-mail: fbao@xmu.edu.cn E-mail:fbao@xmu.edu.cn
作者简介:刘锦生男, 硕士研究生。主要研究方向: 实验流体力学, 数值模拟。 E-mail: 1184997667@qq.com
基金资助:
国家自然科学基金 (11072206)

Experimental study on Rayleigh-Ludwieg instability of aircraft wake vortex

BAO Feng¹, LIU Jinsheng¹, ZHU Rui¹, LIU Yue²

1. School of Physics and Mechanical and Electrical Engineering, Xiamen University, Xiamen 361005, China;
2. Xiamen Institute of Technology, Huaqiao University, Xiamen 361021, China

Received:2015-01-27 Revised:2015-03-30 Online:2015-07-15 Published:2015-04-01
Supported by:
National Natural Science Foundation of China (11072206)

摘要/Abstract

摘要：

以飞机起降过程中主翼和尾翼产生反向涡系存在相互作用的事实为背景,设计了一套反向双漩涡发生装置。通过改变两涡的位置关系与初始涡强度比值,采用流动显示与粒子成像测速(PIV)技术,对涡系相交不稳定性的作用特性进行了研究。结果表明:小涡的引入改变了主涡原有运动轨迹,合理地引入小涡的位置与小涡的强度,对主涡能量的衰减有明显的促进作用,但它们之间不呈现明显的线性关系;涡空间运动轨迹的分析,对未来完善机场起降控制模型有一定借鉴意义;实验结果也为飞机整体设计提供了一定参考依据,在满足飞行力学的设计基础上,优化整体气动布局对降低飞机尾流强度有显著的影响。

关键词: 飞机尾涡, Rayleigh-Ludwieg不稳定性, 流动显示, 粒子成像测速(PIV), 低雷诺数流动

Abstract:

Based on the fact that the main wing and tail would produce counter-rotating vortices in the process of taking-off and landing, a set of double vortex generators are designed. Under two different experimental conditions, in terms of changing the position and initial intensity ratio of the double vortex, the wake vortex development of the test mode is acquired, including flow visualizations and particle image velocimetry (PIV) technology. Research reveals that the introduction of a weaker vortex, with a proper position and initial intensity ratio, would change the main vortex original trajectory and promotes its dissipation. However, it does not present an obvious linear relationship between them. The analysis results of vortex trajectory could be used in improving the efficiency of taking-off and landing in airports, the experiments also provide a reference for the overall design of aircrafts: when the requirement for flight mechanics design is satisfied, optimizing the overall aerodynamic layout will have a significant effect on alleviating the intensity of aircraft wake.

Key words: aircraft wake vortex, Rayleigh-Ludwieg instability, flow visualization, particle image velocimetry (PIV), low Reynolds number flow

中图分类号:

V211.76

鲍锋, 刘锦生, 朱睿, 刘玥. 飞机尾涡系Rayleigh-Ludwieg不稳定性实验研究[J]. 航空学报, 2015, 36(7): 2166-2176.

BAO Feng, LIU Jinsheng, ZHU Rui, LIU Yue. Experimental study on Rayleigh-Ludwieg instability of aircraft wake vortex[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(7): 2166-2176.

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E-mail：hkxb@buaa.edu.cn

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飞机尾涡系Rayleigh-Ludwieg不稳定性实验研究

Experimental study on Rayleigh-Ludwieg instability of aircraft wake vortex

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