超临界翼型Gurney襟翼增升实验研究  

Experimental Investigation into Effects of Gurney Flaps on Supercritical Airfoil

作　　者：李亚臣[1] 王晋军[1] 樊建超[2] 张林[2] 

机构地区：[1]北京航空航天大学飞行器设计与应用力学系 [2]中国空气动力研究与发展中心

出　　处：《北京航空航天大学学报》2003年第6期471-474,共4页Journal of Beijing University of Aeronautics and Astronautics

摘　　要：在FL 2 1风洞中进行了高速情况下Gurney襟翼对超临界翼型增升实验研究 .0 .5 %C、1 .0 %C、1 .5 %C和 2 .0 %C高度的Gurney襟翼分别使翼型最大升力系数提高了 6.0 %、1 2 .4%、2 1 .7%和 2 2 .3%,其中 ,1 .5 %C高度的Gurney襟翼使翼型获得了 33.2 %的最大升阻比增量 .其增升机理则是由于Gurney襟翼前表面压力增强 ,而其下游底部吸力增加 。An experimental study was performed on a supercritical airfoil in the FL-21 wind tunnel to investigate the lift-enhancement effects of the Gurney flaps at high speed conditions. The 0.5% C, 1.0% C, 1.5% C and 2.0% C height Gurney flap increased the maximum lift-coefficient by 6.0%, 12.4%, 21.7% and 22.3% separately, and the 1.5% C height Gurney flap increased the maximum lift-to-drag ratio by 33.2%. The mechanism of this increment in lift is that the pressure upstream of the Gurney flap was increased and the base suction downstream of it was increased also, and this difference in pressure led to an increment in circulation.

关 键 词：超临界机翼 增升装置 风洞试验 GURNEY襟翼 

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]