为改善叶片失速特性，以具有圆弧形缝道的两段式NACA0021翼型为基础研究模型，设计一种导流式翼缝（Flow-deflecting Gap，FDG），研究在不同的导叶设计参数与不同雷诺数下导流式翼缝在多段翼型被动流动控制中的效果。研究发现：导流式翼缝可在一定攻角范围内抑制甚至消除分离涡的生成及发展；当前翼缝宽度为0.03c，后翼缝宽度为0.01c时，最大升力系数可提升5.33%，失速攻角增大2°，出现较大尺度分离涡的攻角增大2°，升力波动载荷大幅降低；在不同雷诺数下，FDG翼型的最大升力系数均有不同程度提升，失速特性均有不同程度改善，升力波动载荷均大幅降低。

In order to improve the stall characteristics of the blade,a twostage NACA0021 airfoil with a circular gap is used as basic model and a flow-deflecting gap (FDG) is designed.The effect of the flowdeflecting gap with different design parameters of guide blade under different Reynolds numbers on the passive flow control of the multielement airfoil is studied.The results show that flowdeflecting gap can suppress or even eliminate the generation and development of separation vortex in a certain range of attack angle.When the width of front gap is 0.03c and width of back gap is 0.01c,the maximum lift coefficient is increased by 1.76% and stall angle is improved by 1°.Moreover,the frequency of vortex shedding is reduced and the fluctuating load of lift is significantly decreased.With different Reynolds number,the maximum lift coefficients have different degrees of improvement.Furthermore,all stall characteristics are improved and all fluctuating loads of lift are dramatically decreased.

TK83

国家自然科学基金（51676131，51176129）