本实验应用染色液流动显示技术和激光测速技术 (LDV)研究了 6 0°后掠三角翼在后缘差动喷流、对称喷流情况下前缘涡破裂位置、涡核的空间分布、涡核的速度分布以及三角翼背风面流动结构随迎角的演化等。实验结果表明 ,喷流增大了三角翼前缘涡涡核保持高速度的区域 ,推迟了涡核减速的位置 ,在大迎角情况下 ,对称喷流有助于消除由前缘涡振荡引起的“摇滚”现象。 In this experiment, the position of vortex rupture, the spatial distribution of vortex nuclei and vortex nuclei in the case of trailing edge differential jet and symmetric jet were studied by using liquid flow display technology and laser velocity measuring technique (LDV) The velocity distribution of the nucleus and the evolution of the flow structure at the leeward of the delta wing with the attack angle. The experimental results show that the jet increases the area where the vortex core at the leading edge of the delta maintains a high velocity and postpones the position where the vortex nucleus decelerates. At high angles of attack, the symmetrical jet helps to eliminate the vortex oscillation induced by the leading edge The “rock” phenomenon.