Control of vortices on a delta wing by leading-edge injection
Control of vortices on a delta wing by leading-edge injection
复制标题
通过前缘喷射控制三角翼上的涡流
DOI：
10.2514/3.11749
复制
发表时间：
1993
期刊：
影响因子：
2.5
通讯作者：
D. Rockwell
中科院分区：
文献类型：
--
作者：
W. Gu;O. Robinson;D. Rockwell
本实验研究了大迎角下半三角翼的绕流控制问题。沿机翼前缘沿切向方向采用稳定吹气、稳定吸气或交替吸风可以显著延缓旋涡破裂和失速的发生。交替吸-吹的最有效周期约为机翼绕流的一个对流时间尺度。这种控制的结果是，横流平面内的旋涡结构从完全失速状态修改为高度相干的前缘旋涡。这种向重新稳定的涡旋的变换由瞬时速度场、流线型和涡度等值线表示。
This experimental investigation addresses the control of flow past a half-delta wing at high angle of attack. Application of steady blowing, steady suction, or alternate suction-blowing in the tangential direction along the leading edge of the wing can retard substantially the onset of vortex breakdown and stall. The most effective period of the alternate suction-blowing is on the order of one convective time scale of the flow past the wing. As a result of this type of control, the vortex structure in the crossflow plane is modified from a fully stalled condition to a highly coherent leading-edge vortex. This transformation to a restabilized vortex is represented by instantaneous velocity fields, streamline patterns, and vorticity contours