控制机翼附面层分离的涡流发生器实验研究  

Experimental investigation of boundary layer separation control for wing using vortex generators

作　　者：张进[1] 张彬乾[2] 段卓毅[3] 焦予秦[2] 

机构地区：[1]南昌航空工业学院,江西南昌330034 [2]西北工业大学,西安710072 [3]中航第一飞机设计研究院,西安710089

出　　处：《南昌航空大学学报（自然科学版）》2006年第1期39-42,共4页Journal of Nanchang Hangkong University(Natural Sciences)

基　　金：国防科工委"十五"计划

摘　　要：本文在微型涡流发生器控制超临界翼型附面层分离实验研究的基础上,在低速风洞中研究了微型涡流发生器弦向位置和安装偏角对超临界机翼附面层分离控制效果的影响。研究结果表明,微型梯形涡流发生器对超临界机翼附面层分离的控制主要起减阻作用;其弦向最佳位置在分离线前约4倍涡流发生器高度之间;最佳安装角为35°。This paper investigates the effect of the chordwise position of microvortex generators and their installation angles on the boundary layer separation control for supercritical wing in the low speed wind tunnel.The results indicate that the principal effect of micro-trapezoid vortex generator is drag saving for boundary layer separation control of supercritical wing.The experimental results also show that the optimum chordwise position was found to be about 4 times micro-vortex generator's height upstream of baseline separation;The optimum installation angle was found to be 35°.

关 键 词：微型涡流发生器 超临界机翼 附面层分离 油流 

分 类 号：V225[航空宇航科学与技术—飞行器设计]