An innovative technique for wing stall control, flow deflector, is studied in the present paper. Numerical simulation for a two dimension airfoil is conducted to study the influence for the height of the flow deflector. The PIV measurement is used for flow visualization and validates the control effect of flow deflector at a lower Reynolds number (Re = 6.32E05 ). Wind tunnel tests based on the results of Numerical simulation and Orthogonal design are carried out to investigate the flow deflector at a higher Reynolds number (Re = 1.76E06 ). All the results indicate that the flow deflector can control the stall of a wing effectively. The deflector is able to restrain the wing's flow separation at high angle of attack, delay stall and enhance lift. The orthogonal analysis for the results of force measurement presents the best level combinations for the average aerodynamics force among angles of attack from 16°to 30°.%介绍了一种控制机翼失速特性的新技术--流动偏转器.通过对二维翼型的数值模拟,研究了流动偏转器高度对控制效果的影响.采用PIV测量作为流动显示手段,验证了较低雷诺数(Re=6.32×10<'5>)时流动偏转器对机翼流动分离的控制效果.基于数值模拟结果和止交设计方法,对流动偏转器在更高雷诺数(Re=1.76×10<'6>)下进行了风洞测力实验研究.研究结果表明,流动偏转器可以有效控制机翼失速特性,能够抑制机翼大攻角下的流动分离,推迟失速攻角和增加升力.对测力实验结果的止交分析还给出了以16°到30°攻角范围内平均气动力最佳为目标的最优水平组合.
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