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本文的研究目的是弄清机翼翼梢涡的结构及安装翼梢扰流片对翼梢涡的影响。研究方法是设计制作了几种不同的扰流片，分别把它们安装到一个基本翼的翼梢上，利用氢气泡显示法在槽中观察了无附加扰流片和安装不同扰流片时翼梢涡的结构和衰减过程；利用激光测速仪在水洞中测量了有无扰流片时翼梢涡的周向速度分布，给出了翼梢涡影响标度的衰减曲线。实验结果表明：扰流片对翼梢涡的初期结构有影响，但对翼梢涡的中、后期发展影响不大
The purpose of this paper is to find out the structure of the wingtip vortex and the effect of wingtip spoiler on wingtip vortex. The research method is to design and fabricate several different spoilers, which are respectively mounted on the wing tips of a basic wing. The hydrogen bubble display method is used to observe the effect of the additional spoiler on the groove and the installation of different spoilers The structure and decay process of tip vortex are analyzed. The circumferential velocity distribution of wing tip vortex with or without turbulent vane is measured by laser velocimeter in water tunnel, and the decay curve of the influence amplitude of wing tip vortex is given. The experimental results show that the spoiler has an impact on the initial structure of the wing tip vortex but has little effect on the development of the wing tip vortex in the mid and late stages