俯仰振荡三角翼前缘涡破碎的流动显示  

Flow Visualization of Leading Edge Vortex Breakdown on Delta Wings

作　　者：李京伯[1] 张庆利[1] 

机构地区：[1]南京航空航天大学

出　　处：《实验力学》1997年第1期119-125,共7页Journal of Experimental Mechanics

基　　金：航空科学基金

摘　　要：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。A flow visualization investigation on leading edge vortex breakdown was carried out for two flat plate delta wings of swept angle 65° and 70° undergoing large amplitude pitching motions in the 1mlow speed wind tunnel at NUA.The wing was sinusoidally pitched at reduced frequencies of 0.03and 0.06,for angle of attack of α=0 to 60 deg.During these dynamic motions,visualization of the leading edge vortices was obtained by injecting TiCl 4 through ports located near model apex.The location of vortex breakdown was recorded using phase locked photography technique.Experimental results showed that when the wing was sinusoidally pitched,hysteresis was observed in the location of vortex breakdown.The propagation velocity of the vortex breakdown location relative to the delta wing was also discussed in this paper.

关 键 词：流动显示 非定常流 大攻角 分离流 飞机 

分 类 号：V211.71[航空宇航科学与技术—航空宇航推进理论与工程]