动失速型非定常分离流的主动控制  

Active Control of Dynamic Stall Type Unsteady and Separated Flow

作　　者：张庆利[1] 李京伯[1] 

机构地区：[1]南京航空航天大学

出　　处：《空气动力学学报》1999年第1期1-7,共7页Acta Aerodynamica Sinica

基　　金：国家自然科学基金

摘　　要：本文对动失速型非定常分离流的主动控制方法在低速风洞中进行了实验研究。在二元平板模型中部安装一作振荡运动的主扰流板产生动失速型非定常分离流；在其上游的模型表面上安装另一控制用的振荡小扰流板，应用非定常流的相平均测压技术，研究前置小扰流板的控制效果。实验结果表明，通过控制两扰流板之间的运动相位差，可以显著影响并改变动失速型分离涡的强度和对流时间特性。在有利的控制相位下，涡的负压峰值最大可降低４８％，涡对流时间最大可推迟０．１９周期。对于间歇振荡的扰流板，采用相位提前控制比相位滞后控制更有效。An experimental investigation on the active control of dynamic stall type unsteady separated flow is carried out in the low speed wind tunnel using a phase averaged pressure measure ment technique.The two dimensional oscillating primary spoiler used to generate the dynamic stall type unsteady separated flow is located in the middle of the flat plate model.In addition,a second small oscillating spoiler used as the control device is added to the upstream of the primary spoiler.Experimental results show that the upsteam control spoiler is exerted an effective control on dynamic stall type vortex structures.The suction peak of the vortex is reduced up to 48%,and the vortex convection time delay as much as 0.19 oscillating period.For the intermittent spoiler motion case the control effect on the dynamic stall type vortex using control phase advance is much greater than that using control phase delay.

关 键 词：动失速 流动控制 非定常 分离流 风洞实验 

分 类 号：V211.5[航空宇航科学与技术—航空宇航推进理论与工程] V211.7