后缘喷流对三角翼前缘涡影响的数值模拟  

Numerical simulation to effects of trailing edge jet on delta wing vortices

作　　者：陈宇[1] 阎超[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100083

出　　处：《北京航空航天大学学报》2007年第10期1170-1173,共4页Journal of Beijing University of Aeronautics and Astronautics

摘　　要：为了研究三角翼后缘对称喷流对前缘涡破裂位置和旋涡结构的影响,通过高分辨率的N-S方程数值模拟方法,对60°后掠角三角翼后缘有对称喷流及无喷流情况下的绕流进行了研究.结果表明,后缘喷流速度与自由来流速度之比影响前缘涡破裂的位置.与无喷流情况相比,喷流与来流速度比的不同造成了涡破裂的提前或推后.而与传统结论有所不同的是,并非所有的后缘喷流都能延迟涡的破裂.另外,后缘对称喷流对涡轴位置的影响很小.后缘对称喷流不改变三角翼前缘涡横截面流动拓扑结构的变化规律,但影响极限环的扩张速度.In order to study the influence of trailing edge symmetrical jet on leading edge vortex breakdown location and flow structure over a delta wing, vortex flows over a 60oswept delta wing with trailing symmetrical edge jet and without trailing edge jet were studied using high precise simulation of N-S equations. The results show that the ratio of jet velocity to free flow velocity affects the location of vortex breakdown. Compared with the condition without jet, the variation of the ratio of jet velocity to free flow velocity determines vortex breakdown location advance or delay. The difference from the traditional opinion is that not every case with trailing edge jet could delay the location of vortex breakdown. In addition, the trailing edge symmetrical jet has little influence on the position of the vortex axis. The trailing edge jet does not change the rule of topological structure transformation of the cross section, but it impacts the velocity of limit ring spread.

关 键 词：三角翼 后缘喷流 涡破裂 极限环 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]