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在飞机飞行的过程中尾涡会伴随着升力产生,威胁后机的飞行安全.在简化机翼模型上添加扰流片,通过一个矩形翼以引入一个与主翼尾涡大小不同、方向相反的小涡,构建尾流自消散四涡系统,以期诱发尾涡的Rayleigh-Ludwig相交不稳定性.通过改变扰流片的大小形状,调整模型的攻角和拖曳速度,采用粒子图像速度场仪测量系统定量研究在低雷诺数下单主翼尾涡发展特性以及双涡相互作用特性.研究表明:在未添加扰流片时,尾涡环量在45个翼展内相对于初始环量基本保持不变;在添加扰流片的情况下尾涡的环量衰减可以达到35%~55%,而未添加的基本翼型的尾涡的环量则几乎保持不变,这说明添加适当的扰流片能诱发尾涡的Rayleigh-Ludwig相交不稳定性,加速尾涡的消散,当小涡和主涡的初始环量比为-0.489、初始距离比为0.5时,45个翼展范围内,尾涡环量衰减55.9%.本文系统性的实验结果可以为低尾流机翼的设计提供参考依据.
In the process of aircraft flight, the wake will be accompanied by the lift, threatening the flight safety of the rear airplane. Adding a spoiler to the simplified wing model through a rectangular wing to introduce a small vortex of opposite size to that of the main wing , To construct a wake-self-dissipating four-vortex system in order to induce the Rayleigh-Ludwig’s intersection instability of the wake.We change the angle of attack and the velocity of the model by changing the size and shape of the spoiler, and use the particle image velocity field measurement system to quantify The development of single main wing wake vortex at low Reynolds number and the characteristic of double vortex interaction are studied. The results show that when no spoiler is added, the amount of wake vortex ring remains constant with respect to the initial ring volume at 45 wingspan. The vortex shedding vortex shedding can reach 35% ~ 55% with the addition of the spoiler, while the vortex shedding of the basic airfoil with no added voids remains almost unchanged, which shows that adding appropriate spoiler When Rayleigh-Ludwig intersection vortex instability induced vortex eddies, the wake vortex dissipates. When the initial ring ratio of small vortex and main vortex is -0.489 and the initial distance ratio is 0.5, The amount of decline of 55.9%. This article is a systematic reality Results provide evidence for a low wake wing design.