前缘缝翼开缝改善增升装置失速特性研究  

Stall characteristics of high-lift device improved by slotting on leading-edge slat

作　　者：刘中元 褚胡冰 陈迎春[3] 毛俊[3] 张彬乾[1] LIU Zhongyuan;CHU Hubing;CHEN Yingchun;MAO Jun;ZHANG Binqian(School of Aeronautics,Northwestern Polytechnical University,Xi’an 710072,China;Marine Design&Research Institute of China,Shanghai 200011,China;Shanghai Aircraft Design and Research Institute,Commercial Aircraft Corporation of China Ltd,Shanghai 200235,China)

机构地区：[1]西北工业大学航空学院,西安710072 [2]中国船舶及海洋工程设计研究院,上海200011 [3]中国商飞上海飞机设计研究院,上海200235

出　　处：《空气动力学学报》2023年第2期21-28,I0001,共9页Acta Aerodynamica Sinica

基　　金：中央高校基本科研业务费专项资金(3102019JC009,G2016KY0002)。

摘　　要：大型民机高升力构型多采用多段式增升装置,大迎角飞行时,前缘缝翼上表面可能出现流动分离,造成缝翼尾迹流区迅速增厚,加剧缝翼与下游翼段气流的交混作用,导致各翼段环量减小、升力下降,最终发展为失速。针对多段式增升装置大迎角失速问题,本文基于有限体积RANS方法,研究了前缘缝翼开缝改善增升装置失速特性的作用机理与参数影响规律。研究发现:前缘缝翼开缝可有效推迟缝翼流动分离的发生,抑制缝翼尾迹区发展及缝翼与下游翼段附面层气流的交混,减缓对襟翼流动的不利影响,显著改善增升装置失速特性;开缝位置及射流出口方向对前缘缝翼流动的控制效果影响明显,应根据前缘缝翼形状和工作状态合理设计前缘缝翼开缝方案,以便获取更好的气动性能收益。High-lift devices are widely used on multi-element wings of large civil aircrafts. At large angles of attack, flow separation may occur over upper surfaces of leading-edge slats of multi-element airfoils. The flow separation would increase the thickness of the induced wake flow rapidly and enhance the interaction between the wake and the downstream boundary. This will reduce the circulation and lift and finally result in the stall.This paper puts forward a method to improve the aerodynamic performance of high-lift devices by slotting on leading-edge slats. Flow fields and parametric effect of the slotting are investigated based on numerical simulations by solving Reynolds-Averaged Navier-Stokes equations. Results show that the slots on leading-edge slats can effectively delay the flow separation by inhibiting the development of the wake flow and its interaction with downstream boundary layers. The adverse impact induced by the stall can be alleviated significantly as a result. However, the control effect is closely related to the slot position and the direction of the exiting jet.Therefore, to obtain a favorable improvement of aerodynamic performance, the slot should be reasonably designed according to the shape of the leading-edge slat and also to the surrounding flow field.

关 键 词：增升装置 流动分离 流动控制 前缘缝翼开缝 数值模拟 

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]