偏转矢量喷流对双三角翼前缘涡破裂影响的实验研究  

Experimental Investigation for the Effects of Vectored Trailing-Edge Jets on the Leading-Edge Vortex Breakdown of a Double Delta Wing

作　　者：王晋军[1] 秦永明[1] 

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》2001年第4期372-377,共6页Journal of Experimental Mechanics

基　　金：国家教育部高等院校博士学科点基金资助项目的部分成果 (项目编号 :971 3)

摘　　要：本文应用染色液流动显示技术对后缘偏转喷流情况下 76°/4 0°双三角翼前缘涡破裂位置的变化进行了观测 ,实验结果表明偏转喷流主要推迟与喷流方向相同一侧前缘涡的破裂 ,而使另一侧前缘涡破裂略有提前 .随着喷流偏转角度的增大 ,喷流使两前缘涡破裂位置差逐渐增大 .另外 ,随着模型攻角的增大 ,前缘涡涡核与双三角翼翼面的夹角逐渐增大 。Dye-injection flow visualization technique is used to observe the leading-edge vortex breakdown of a double delta wing with the leading-edge vectored jets. It is found that the vectored jet may delay the leading-edge vortex breakdown in the jet direction, and makes the other leading edge vortex breaking down somewhat early, besides, the difference in the two leading-edge vortex breakdown positions increases with the jet angle. It is also found that with the increase of the angle of attack, the angle between the double delta wing surface and the leading-edge vortex increases, which leads to the action of vectored jets on the vortex breakdown weakened.

关 键 词：双三角翼绕流 流动显示 涡破裂 矢量喷流 染色液流动显示技术 偏转矢量喷流 推动矢量控制技术 

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] O351.3[理学—流体力学]