76°/40°双三角翼前缘涡破裂及其控制实验研究  

Experimental Studies on Leading-Edge Vortex Breakdown and Control of Flow over 76°/40° Double Delta Wing

作　　者：王晋军[1] 刘激瀛[1] 薛启智[1] 

机构地区：[1]北京航空航天大学飞行器设计与应用力学系

出　　处：《北京航空航天大学学报》2001年第1期51-53,共3页Journal of Beijing University of Aeronautics and Astronautics

基　　金：国家教育部博士点基金资助项目!( 9713 );国家部委基金资助项目

摘　　要：流动显示结果表明 ,喷流能有效地推迟双三角翼前缘涡的破裂 ,且随着攻角的增大 ,前缘涡破裂位置逐渐推后 ,喷流极大地改善了大攻角情况下前缘涡的非对称破裂特性 ,能有效地克服可能出现的机翼的“摇滚”现象 .另外 ,后缘喷流可以减弱乃至消除前缘涡混掺现象的发生 ,进而有利于飞行器的操纵 .The flow visualization techniques has been used to investigate the effects of trailing-edge jets on the leading-edge vortex breakdown and its control of flow over a 76°/40° double Delta wing. The experimental results indicate that the trailing-edge jets can delay the leading-edge vortex breakdown efficiently, and this delay increases with the angle of attack. The trailing-edge jets can greatly improve the asymmetrical characteristics of the leading edge vortex breakdown at large angle of attack, and the possible occurrence of rock phenomenon may be overcome. In addition, the trailing-edge jets may weaken or even eliminate the mixing phenomenon of the leading-edge vortex, which is in advantage of the flight control of aircraft.

关 键 词：涡旋流动 流动显示 双三角翼绕流 流动控制 前缘涡破裂 后缘喷流 机翼 

分 类 号：V211.41[航空宇航科学与技术—航空宇航推进理论与工程]