民用支线飞机失速特性优化中关于机翼上表面涡流发生器的研究  

Research on vortex generator on wing upper surface in optimization of stall characteristics of civil regional aircraft

作　　者：李秋捷[1] 蒋晓莉[1] 周星[1] 钟园[1] LI Qiujie;JIANG Xiaoli;ZHOU Xing;ZHONG Yuan(Shanghai Aircraft Design and Research Institute,Shanghai 201210,China)

机构地区：[1]上海飞机设计研究院,上海201210

出　　处：《民用飞机设计与研究》2022年第3期47-55,共9页Civil Aircraft Design & Research

摘　　要：飞机在飞行过程中迎角超过临界值后,机翼上表面原本附着的气流开始发生大面积分离,此时升力系数随着迎角的增大反而下降,这种现象称作失速。当飞机失速时,操控会受到很大的影响,是一种危险的飞行状态。某民用支线飞机在试飞中发现失速特性主要受滚转失速的影响,在达到最大升力系数之前就出现了不可接受的失速特性,失速进入过程中,副翼操纵效率降低较快,快接近失速时飞机出现急剧的滚转。涡流发生器在民机中有广泛的应用,可以改善机翼的流动分离从而提高失速特性,并且有改动小、可行性高等优点。拟通过在机翼上表面安装涡流发生器的方法来改善某民用支线飞机的失速特性。利用数值计算等方法设计出涡流发生器的位置、高度、偏角以及数量等参数。通过低速高雷诺数风洞试验来验证涡流发生器的实际效果,最后得出几种效果可观的涡流发生器方案。When the angle of attack exceeds the critical value during flight of aircraft, the air flow attached to the upper surface of the wing begins to separate in a large area. At this time, the lift coefficient decreases with the increase of the angle of attack, which is called stall. When the plane stalls, the control is greatly affected so it is a dangerous flying condition. During the test flight of a civil regional jet, it was found that stall characteristics were mainly affected by rolling stall, and unacceptable stall characteristics appeared before the maximum lift coefficient was reached. In the stall entering process, aileron control efficiency decreased rapidly, and the aircraft rolled sharply when approaching stall. Vortex generators are widely used in civil aircraft, which can improve the flow separation of wings and thus improve stall characteristics, and have the advantages of small modification and high feasibility. In this paper, the stall characteristics of a regional jet were improved by installing vortex generators on the upper surface of the wing. The position, height, deflection angle and quantity of vortex generator were designed by numerical calculation. Through low speed and high Reynolds number wind tunnel test, the actual effect of vortex generator was verified. Finally, several effective schemes of vortex generator were obtained.

关 键 词：失速特性 涡流发生器 风洞试验 

分 类 号：V211.41[航空宇航科学与技术—航空宇航推进理论与工程]