空气动力学学报2013，Vol.31Issue(1)：9-14,6.DOI:10.7638/kqdlxxb20130102
有限翼展机翼失速特性控制研究
Researches of a finite-span wing stall control
摘要
Abstract
For controlling the flow separation on the wing at high angle of attack, an innovative technique for a finites-span wing stall control, flow deflector, is studied in the present paper.Wind tunnel experiments are conducted to validate the reliability of the numerical simulation.The comparison between them indicates that the flow deflector can control the stall of a wing and restrain the flow separation effectively at high angle of attack.Deep research of flow direction changing trend and boundary layer are carried out to investigate the mechanism of flow deflector.The results indicate that the flow deflector increase the angle of flow around the leading edge of the wing and decrease the angle of the coming flow to make it deflect to the upside of the wing.The flow deflector can suppress the three dimensional effects and maintain the two-dimensional flow characteristics to some extent.Furthermore, the flow deflector can easily change the velocity profile in the boundary layer and make it more "fuller".It decreases the shape factor and increases the stability of the boundary layer to restrain the flow separation.关键词
流动控制/流动偏转器/测力实验/数值计算/增升/翼型Key words
flow control/ flow deflector/ force measurement/ numerical simulation/ lift enhancement/airfoil分类
航空航天引用本文复制引用
白亚磊,李鹏..有限翼展机翼失速特性控制研究[J].空气动力学学报,2013,31(1):9-14,6.基金项目
国家973项目资助(2007CB714600) （2007CB714600）
