有限翼展机翼失速特性控制研究  

Researches of a finite-span wing stall control

作　　者：白亚磊[1] 李鹏[1] 

机构地区：[1]南京航空航天大学空气动力学系,江苏南京210016

出　　处：《空气动力学学报》2013年第1期9-14,共6页Acta Aerodynamica Sinica

基　　金：国家973项目资助(2007CB714600)

摘　　要：针对有限翼展机翼大迎角下的流动分离情况,研究了一种新型流动控制技术———流动偏转器。通过风洞实验和数值计算相结合的方法,既验证了计算的准确性,又阐述了流动偏转器可改善机翼大迎角失速特性的作用。通过对流动方向变化规律和翼面边界层的深入研究,探寻了流动偏转器的控制原理:使来流向机翼吸力面偏转;削弱机翼前缘附近流动的三维效应使流动趋近二元化;使边界层内速度型变得饱满,减小速度型形状因子H12,增大速度型的稳定性,抑制流动分离。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 i 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 

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]