大型飞机平尾翼尖涡对后体涡系影响的实验研究

大型飞机在飞行过程中机身后体会产生一对反向旋转的脱体涡（后体主涡），该涡与平尾翼尖涡共同构成飞机后体的涡系结构。在风洞中，利用激光粒子测速（PIV）方法，对单独后体和加装不同展长平尾的后体，分别研究涡系结构的动力学特征。结果表明:后体主涡的涡核中心沿流向明显向上移动；加装平尾后，涡系呈现典型的四涡结构，平尾翼尖涡对后体主涡影响显著，加大了后者向上移动的趋势，同时使其沿展向外移，并显著削弱其涡旋强度；平尾展长增加后，后体主涡受到的影响有所减弱。在低速环境下，来流速度对后体涡系结构的无量纲动力学参数影响较小。

Experimental investigation on large aircraft afterbody vortices under the influence of horizontal tail tip vortices

The vortex system of a large aircraft afterbody includes a counter-rotating vortex pair (APV) generated by the afterbody separated flow and horizontal tail tip vortices (HTV). The characteristics of the vortices of a simplified afterbody with and without horizontal tails were measured in the wind tunnel using PIV. APV shifts upwards when moving downwards. A four-vortex system is observed for the afterbodies with horizontal tails. APV is significantly affected by HTV:APV shifts upwards faster and moves outwards in spanwise direction; the existence of HTV strongly reduces the vorticity strength of APV. The restraint effect becomes stronger as the span of horizontal tail decreases. Inflow speed has little to do with non-dimensional parameters of the vortices under low speed conditions.