等速上仰翼型尾部流动观察及动态失速机理探讨  

THE TRAILING-EDGE VORTEX STRUCTURE OF A CONSTANT-RATE AIRFOIL AND MECHANISM OF DYNAMIC STALL

作　　者：孙茂[1] 王家禄[1] 连淇祥[1] 

机构地区：[1]北京航空航天大学流体力学研究所,北京100083

出　　处：《力学学报》1993年第5期628-631,共4页Chinese Journal of Theoretical and Applied Mechanics

摘　　要：在尾缘处置氢气泡铂丝,观察了上仰翼型自尾缘流入尾迹的涡层。基于尾涡层及(以往)上翼面分离涡的观察,用涡动力学理论,探讨了动态失速的机理,并解释了新的失速现象。The vortex structure shed from the trailing-dege of a constant-rate pitching airfoil was visualized using hydrogen bubble technique. Its time evolution, and the effects of pitching rate were studied. Combining the trailing-dege vortex structure with the (previously obtained) airfoil upper-surface separated vortex structure, a complete flow structure was obtained. The mechanism of dynamic stall was studied based on the flow structure and vorticity dynamics theory, and insights were provided.

关 键 词：上仰翼型 尾涡层 动态失速 

分 类 号：V211.41[航空宇航科学与技术—航空宇航推进理论与工程]