流动偏转器对NACA0012机翼增升实验研究
首发时间:2017-05-16
摘要:对naca00流动偏转器对NACA0012机翼增升实验研究流动偏转器对NACA0012机翼增升实验研究12机翼加装流动偏转器进行了风洞实验研究。实验结果表明:流动偏转器能有效控制机翼上表面的流动分离。为了得到较好的气动效果,文中采用正交实验方法对偏转器的参数进行优化。优化偏转器可使机翼失速攻角从14 推迟到18 ,并且可以在不损害小攻角升力系数线性特征的情况下,提高最大升力系数。流动偏转器适合应用在中高升力系数情况(如起飞,降落等),在小升力系数下不宜使用。
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Experimental Investigation of Lift En-hancement on a NACA0012 Wing Using Flow deflector
Abstract:An experimental wind tunnel investigation was undertaken to determine the effects of Flow deflector on a NACA0012 rectangular wing. The results of the wind tunnel experiments indicate that this new technique of flow control is efficient for flow separation control on the upper surface of the rectangular wing with airfoil of NACA 0012. The orthogonal design, as an optimization method, was used to choose the best parameter set to optimize the aerodynamic performance. With this parameter set, the stall angle of attack of the wing could be delayed from 14 to 18 and the maximum lift coefficient could be increased, while the linear characteristics for the lower angle of attack is kept. The Flow deflector should be employed at moderate-to-high lift-coefficient conditions such as takeoff and landing, while not advisable at low-to-moderate lift-coefficient conditions.
Keywords: lift enhancement flow deflector wind tunnel rectangular wing airfoil
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