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飞机尾涡是与升力相关的固有流动现象,威胁着机场附近的飞行安全,同时也限制了机场使用效率。在矩形机翼翼尖以一定方式安装涡流发生器,产生与主涡旋向相反的小涡,来构建一种具有自我消散机制的四涡系统,能实现尾涡集中能力的快速消散。结合流动显示和粒子成像测速(PIV)测量,探索了在不同的参数匹配下,下游25个翼展范围内该四涡系统的空间发展过程、涡量发展曲线,以及45个翼展范围内主涡环量的衰减程度。实验结果表明,受小涡诱导,尾涡出现了相交不稳定性,主涡提前破裂,涡量随之降低。当小涡和主涡的初始环量比为-0.581、初始距离比为0.5时,45个翼展范围内,主涡环量衰减34.7%。该实验结果为低尾流机翼的设计提供了一定的参考。
Tail vortexes are inherent flows associated with lift, threatening flight safety near airports, and also limiting airport efficiency. In the rectangular wing tip installed in a certain way vortex generator, the vortex and the main vortex to produce the opposite of the small vortex, to build a self-dissipating mechanism of the four-vortex system, tail vortex concentration ability to achieve rapid dissipation. Combining with flow visualization and particle image velocimetry (PIV) measurements, the space development process, vorticity development curve and the span of 45 wingspan of the four vortex systems in the downstream 25 wingspan were explored with different parameters matching. The degree of vortex ring attenuation. The experimental results show that the vortex instability occurs in the wake vortex induced by the small vortex, and the main vortex ruptures ahead of time and the vorticity decreases. When the initial ratio of the small vortex to the main vortex is -0.581 and the initial distance ratio is 0.5, the main vortex ring attenuation decreases by 34.7% in 45 span. The experimental results provide a reference for the design of low wake flow wing.