后缘喷流对三角翼前缘涡的影响  

The Effects of Trailing Edge Jets on the Vortex Breakdown of a Delta Wing

作　　者：王晋军[1] 苗福友[1] 钮珍南[2] 薛启智[1] 

机构地区：[1]北京航空航天大学流体力学研究所,北京1000832 [2]北京大学湍流研究国家重点实验室,北京100871

出　　处：《空气动力学学报》2000年第2期125-131,共7页Acta Aerodynamica Sinica

基　　金：国防科技预研基金;教委博士点基金;北京大学湍流国家重点实验开放基金

摘　　要：本实验应用染色液流动显示技术和激光测速技术 (LDV)研究了 6 0°后掠三角翼在后缘差动喷流、对称喷流情况下前缘涡破裂位置、涡核的空间分布、涡核的速度分布以及三角翼背风面流动结构随迎角的演化等。实验结果表明 ,喷流增大了三角翼前缘涡涡核保持高速度的区域 ,推迟了涡核减速的位置 ,在大迎角情况下 ,对称喷流有助于消除由前缘涡振荡引起的“摇滚”现象。The dye injection and Laser Doppler Velocimeter (LDV) techniques have been used to investigate the flow over a delta wing with swept of 60°. The content includes the effects of trailing edge differential and symmetric jets on the breakdown position of leading edge vortex, the spatial distribution and the velocity distribution of the vortex core and the evolution of the flow structure with angle of attack. The experimental results indicate that the jets not only increase the region where the leading edge vortex core persists higher velocity and also delay the location where the leading edge vortex core begin to speed down. Moreover, the symmetric jets are helpful to delimitate the “rocking” phenomenon induced by the oscillation of the leading edge vortex at high angles of attack.

关 键 词：三角翼绕流 后缘喷流 涡破裂 流动显示 LDV测量 

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]