60°三角翼前缘涡破裂及其控制实验研究  

Experimental Investigation on the Leading edge Vortex Breakdown and Their Control for Flow over a 60° Delta Wing

作　　者：刘激瀛[1] 王晋军[1] 薛启智 

机构地区：[1]北京航空航天大学流体力学研究所,北京100083

出　　处：《实验力学》2000年第2期206-210,共5页Journal of Experimental Mechanics

基　　金：国防科技预先研究基金;国家教育部博士点基金的资助

摘　　要：本文应用流动显示技术对矢量差动喷流情况下 6 0°三角翼前缘涡破裂特性进行了实验研究 ,结果表明 :矢量差动喷流可以有效地控制前缘涡的破裂位置 ,且整个流场主要受喷流速度大的喷流的影响 ,该侧前缘涡的破裂位置随喷流速度的增大向下游发展 ,而另一侧前缘涡的破裂则提前发生 ;另外 ,在喷流速度差一定的情况下 ,喷流速度越小 ,对前缘涡的控制作用越明显 .The flow visualization technique was used to investigate the effects of the vectored differential trailing edge jets on the leading edge vortex breakdown for flow over a 60° delta wing. The experimental results indicated that the differential vectored trailing edge jets can control the position of vortex breakdown efficiently, and the flow field mainly influenced by the jet with large velocity. With the increase of jet velocity, the jets make the leading edge vortex break down delay in the side of large jet velocity, and cause another leading edge vortex break down early. Moreover, for the fixed differences between the two jet velocities, the less the jet velocity, the more obvious the control effect on the leading edge vortices.

关 键 词：三角翼绕流 流动显示 涡破裂 飞机 

分 类 号：O351.3[理学—流体力学] V211.41[理学—力学]