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前缘后掠角为６５°和７０°的两个平板三角翼作俯仰振荡运动，前缘涡破碎的流动显示实验研究在南京航空航天大学１米低速风洞中进行。俯仰振荡运动的攻角范围为０°～６０°，折合频率为０．０３和０．０６。采用四氯化钛发烟技术显示前缘涡核轨迹及涡破碎位置。流动显示图形采用相位锁定照相记录。实验结果表明大幅俯仰振荡三角翼的动态涡破碎的弦向位置明显滞后于相应攻角下的静态位置，此滞后量随折合频率增加而增大。本文也根据测得的涡破碎位置随攻角变化曲线讨论了涡破碎位置的传播速度
Two slab triangular wings with leading edge sweep angles of 65 ° and 70 ° are used for pitching oscillations. The experimental study on the flow vortex broken by the leading edge is carried out in a 1m low speed wind tunnel at Nanjing University of Aeronautics and Astronautics. The range of angle of attack of pitch oscillation is 0 ° ~ 60 °, and the equivalent frequencies are 0.03 and 0.06. The use of titanium tetrachloride smoke technology shows the vortex core trajectory and vortex broken position. Flow display graphics using phase-locked camera records. The experimental results show that the chordwise position of the dynamic vortex crushing of the large pitch-oscillating delta wing significantly lags behind the static position under the corresponding angle of attack, and this lag increases with the increasing of the frequency of the perturbation. In this paper, we also discuss the velocity of vortex crushing based on the measured curve of vortex crushing with the angle of attack