三角翼后缘喷流对前缘涡破裂位置的影响  

The effects of trailing edge jets on the vortex breakdown location over a delta wing

作　　者：阎超[1] 周禹[1] 谢子贤[1] 陈宇[1] 

机构地区：[1]北京航空航天大学国家计算流体力学实验室北京100191

出　　处：《空气动力学学报》2009年第5期561-565,共5页Acta Aerodynamica Sinica

摘　　要：采用高分辨率的N-S方程数值模拟方法,研究了亚声速来流条件下对称喷流、差动喷流、矢量喷流对60°后掠角三角翼前缘涡破裂位置的影响。结果表明,对称喷流条件下,喷流与来流的速度比影响前缘涡破裂位置;差动喷流情况下,速度大的一侧喷流对涡破裂位置起主要影响;矢量喷流情况下,喷流方向对涡破裂位置影响显著,喷流方向与涡轴方向一致时,涡破裂位置延迟量最多。The effects of the trailing edge jet on the location of leading edge vortex breakdown over a 60° sweep delta wing at subsonic free flow are studied by solving the three dimensional Navier-Stokes equations. The used trailing edge jets include symmetrical jet, differential jet and vectored jet. It is found that the ratio of jet velocity to free flow velocity vi/v∞ affects the vortex breakdown location in symmetrical jet condition, which is different from tradition conclusions in water tunnel. In the case of the differential jet, the vortices breakdown locations are mostly determined by the jet with relative bigger speed. The angle of the jet has a dramatic effect on the vortex breakdown location when the vectored jet is selected. The vortex breakdown location is delayed most when the jet direction is consistent in the vortex axis position.

关 键 词：三角翼 对称喷流 差动喷流 矢量喷流 涡破裂 

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]