动失速型非定常分离涡结构的控制  

Control of Unsteady Separated Vortex Flow of Dynamic Stall Type

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》1998年第1期20-27,共8页Journal of Experimental Mechanics

基　　金：国家自然科学基金

摘　　要：本文对动失速型非定常分离涡结构的控制方法，在低速风洞中应用相平均测压技术进行了实验研究。在二元平板模型中部安装一作俯仰振荡的扰流板产生动失速型分离涡，在其上游安装另一用作控制的小扰流板。实验结果表明，应用前置的振荡小扰流板可影响并改变动失速分离涡的强度和对流特性。在最有利的控制相位下，涡吸力峰可降低４８％，涡对流时间可以推迟０．１９周期。对于间歇式振荡扰流板，采用相位提前控制方式比相位滞后控制方式更有效。Experimental investigation on the control of dynamic stall type vortex flow was made in a low speed wind tunnel by using phase averaged pressure measurement technique. The oscillating primary spoiler used to generate the dynamic stall type vortex was located in the middle of the two dimensional flat plate model, and a small second oscillating spoiler used as the control device was installed upstream of the primary spoiler. Experiments showed that the upstream small spoiler was effective in controling the downstream vortex flow. In a favourable operating condition, the suction peak of the unsteady separated vortex was reduced up to 48%, and the vortex convection time delayed as much as 0 19 oscillating period. It was also found that for intermittent motion of control spoiler, phase advance control was more effective than phase delaying control.

关 键 词：动失速 涡流控制 非定常分离流 机翼理论 

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]