翼梢涡的结构与控制方法探索

The Structure of Wingtip Vortex and Investigation for the method of Wingtip Vortex Control

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。

The structure of wingtip vortex and the affection of tap on wingtip vortex is investigated in this paper.Several taps of different shapes are mounted on the tip of a wing respectively.The structure and the damping process of wingtip vortex is observed when it is visualized by the use of hydrogen bubbles in a towing tank in the case of no tap or different taps.The circumferential velocity is measured through LDV in a water tunnel. The damping process of the intensity of the influence of wingtip vortex on a following airplane is presented on the base of the measured circumferential velocity profile.It is found that the structure of wingtip vortex in earlier stage will be influenced by the taps,but in middle stage or later stage it will be influenced very little.