大型飞机平尾翼尖涡对后体涡系影响的实验研究  

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

作　　者：王笑 秦苏洋 向阳[1] 王福新[1] 刘洪[1] Wang Xiao;Qin Suyang;Xiang Yang;Wang Fuxin;Liu Hong(School of Aeronautics and Astronautics,Shanghai Jiao Tong University,Shanghai 200240,China)

机构地区：[1]上海交通大学航空航天学院,上海200240

出　　处：《实验流体力学》2018年第4期53-60,共8页Journal of Experiments in Fluid Mechanics

基　　金：国家重点基础研究发展计划(2014CB744800)

摘　　要：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。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.

关 键 词：大型飞机 后体 涡系结构 激光粒子测速 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程] O355[理学—流体力学]