矢量喷流对65°三角翼前缘涡破裂的影响  

The effects of vectored jet on leading edge vortex breakdown of 65° delta wing

作　　者：王晋军[1] 刘激瀛[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：《流体力学实验与测量》2000年第3期61-65,共5页Experiments and Measurements in Fluid Mechanics

基　　金：教育部博士点基金;国防科技预研基金资助项目

摘　　要：用流动显示技术研究矢量单喷流对65°尖前缘三角翼前缘涡破裂影响的实验结果表明，偏转角度小于10°时，矢量喷流对前缘涡破裂的影响很小；随着喷流偏转角的增大，喷流对流动控制的作用越来越大，喷流使喷流偏转方向一侧前缘涡破裂位置的延迟量增大，而另一侧前缘涡有提前破裂的趋势。在相同的喷流情况下，随着攻角的增大，喷流的控制效果有减弱的趋势；另外当攻角 α =40°时，很小的喷流就可以使前缘涡由左右掺混变为喷流方向的单向运动。The flow visualization technique has been used to study the effects of vectored single jet on the leading edge vortex breakdown of 65° delta wing. The experimental results indicate that there is a little effect of the jet on the leading edge vortex breakdown when the angle of the vectored jet is less than 10°. With the increase of the vectored angle, the effect of the jet on the flow control becomes stronger, i.e. the jet makes the leading edge vortex breakdown delay in the direction of the vectored jet, and make another leading edge vortex breakdown early. In the case of the same vectored jet, the control effects of the jet tend to be weak with the increase of the angle of attack. Moreover, a little jet can make the mixed leading edge vortex flow to be come the single motion in the jet direction when α =40°.

关 键 词：矢量喷流 涡破裂 流动显示 流动控制 三角翼 

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] O351.3[理学—流体力学]