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中文摘要：
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。
英文摘要：
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.
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