微型飞行器低雷诺数流场显示试验研究  

Flow visualization experiments of MAV in low Reynolds number

作　　者：史志伟[1] 李晨[1] 昂海松[1] 

机构地区：[1]南京航空航天大学航空宇航学院,南京210016

出　　处：《实验流体力学》2008年第2期34-39,共6页Journal of Experiments in Fluid Mechanics

摘　　要：在南航非定常风洞内,对一盘状微型飞行器的气动特性进行了测力和流场显示实验,给出了不同迎角下微型飞行器的空间流场显示结果。研究表明:随着迎角的增加,在机翼上表面开始形成前缘分离涡,并且前缘涡的尺度和强度不断增加。迎角继续增大,前缘涡首先在后缘开始破裂,并不断前移,最终导致微型飞行器的失速。模型上前缘分离涡的形成、发展和破裂是导致盘状微型飞行器气动力特性产生变化的根本原因。The aerodynamic characteristics and flow field visualizations of a MAV are investigated in NUAA unsteady wind tunnel. The results show that the leading-edge vortex form at low angles of attack first. The scales of the vortex are enlarged and the strength is enhanced with the angle of attack increasing. But the lead- ing-edge vortex breaks down at the trailing-edge quickly, when angle of attack continually increasing, the position of vortex breakdown moves upstream. Finally the MAV stalls when the leading-edge vortex breaks down at the whole upper surface. The appearance, development and breakdown of the leading edge vortex are the important factors for the aerodynamic characteristics of this MAV.

关 键 词：微型飞行器 流动显示 前缘涡 低雷诺数 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]