微型涡流发生器控制超临界翼型边界层分离实验研究  

Investigation of boundary layer separation control for supercritical airfoil using micro vortex generator

作　　者：张进[1] 张彬乾[1] 阎文成[1] 段卓毅[2] 陈迎春[2] 焦予秦[1] 于新[2] 

机构地区：[1]西北工业大学,西安710072 [2]中航第一飞机设计研究院,西安710089

出　　处：《实验流体力学》2005年第3期58-60,84,共4页Journal of Experiments in Fluid Mechanics

摘　　要：在低速风洞中研究了微型涡流发生器对超临界翼型边界层分离的控制.根据超临界翼型边界层分离特性,提出了涡流发生器的流动机理.研究了梯形涡流发生器不同高度和弦向位置对边界层分离控制效果的影响.研究表明,微型涡流发生器对超临界翼型边界层分离的控制主要起减阻作用;适宜采用微型涡流发生器对超临界翼型边界层分离进行控制,其最佳位置应在分离线前2～5H涡流发生器高度之间.This paper describes the investigation of boundary layer separation control for supercritical aerofoil using micro vortex generator in the low speed wind tunnel. According to the character of boundary layer separation of the supercritical aerofoil, the flow mechanism of micro vortex generator and the flow separation control effectiveness of the different trapezoid vortex generator height and chordwise position on the supercritical airfoil has been studied. The results indicate that the principal effect of micro trapezoid vortex generator is the reduction in the drag of supercritical aerofoil. The experimental results also show that the optimum effective position range was found to be 2H to 5H of micro vortex generator height upstream of baseline separation.

关 键 词：微型涡流发生器 边界层分离 超临界翼型 

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]