大型民用运输机短舱涡流片增升效率以及参数影响研究  

Investigation on Influence of Nacelle Chine of Large Civil Transport Aircraft on High-Lift Efficiency and on Influence of Relevant Parameters

作　　者：白俊强[1] 刘南[1] 邱亚松[1] 陈迎春[2] 李亚林[2] 周涛[2] 

机构地区：[1]西北工业大学航空学院,陕西西安710072 [2]上海飞机设计研究院,上海200232

出　　处：《西北工业大学学报》2013年第4期522-529,共8页Journal of Northwestern Polytechnical University

摘　　要：采用经风洞试验验证的CFD计算方法和网格生成策略,以某型大型民用运输机基本三段增升装置着陆构型为对象,研究短舱涡流片及其参数对增升装置效率的影响。研究表明:短舱涡流片的流动机理与大后掠三角翼类似,其所诱导漩涡流动的强度、上下位置以及展向位置是影响增升效率的3个关键因素。空间涡下移、向机翼外侧移动或增加其强度均可以提高增升装置的效率。其中涡流片下偏会使空间涡下移且向机翼内侧移动,但是对机翼上方空间涡强度的影响并不是单调的;涡流片后移可以增强机翼上方空间涡强度并使其下移,但是也会造成空间涡向机翼内侧移动;增加涡流片的安装角或者倾角可以增强机翼上方空间涡强度并使其向机翼外侧移动,但是会造成空间涡上移;增加涡流片的后掠角(即减小其前缘附近的面积)使空间涡下移并向机翼外侧移动,但是会造成空间涡强度减弱。所以这些参数(上下位置、前后位置、安装角等)对全机升力系数的影响都不是单调的,需要大量的流场分析方能找到较优的参数组合。同时短舱涡流片还会受到巡航状态、发动机反推和结构等方面的约束,设计过程中需要综合考虑各种影响因素。Carefully considering the landing configuration of a large civil transport aircraft, we apply the CFD com- putational method and mesh generation strategy, whose validity is confirmed by wind tunnel experiments conducted by us, to study the influence of nacelle chine on high-lift efficiency. The results show that the flow mechanism of nacelle chine is similar to that of large sweep delta wing. The intensity and the location of vortex flow, which are induced by nacelle chine, are the key elements of high-lift efficiency. Moving the vortex outer or downward or en- hancing its intensity can increase high-lift efficiency. Through putting nacelle chine downward, the vortex will be moved downward and outboard of wing, but the influence of intensity will not show a monotonic way. The vortex will move upward and inboard of wing and its intensity will be enhanced by putting nacelle chine backward. In- creasing the angle incidence or obliquity of nacelle chine can move the vortex upward and outboard of wing, and both of them can increase the intensity of vortex. Increasing the sweep angle （ reducing the area near leading edge） of nacelle chine will move the vortex downward and outboard of wing, but its intensity will be reduced. Therefore, the influence of these parameters （location, angle of incidence and so on） upon high-lift efficiency are not mono- tonic. Getting the optimum parameter combination needs a lot of analysis of flow fields. Besides, the design of na- celle chine will be restricted by cruise configuration, the reverse thrust device and the structure of engines; they must be taken into consideration in design process.

关 键 词：计算流体力学 运输类飞机 流场 漩涡流动 增升装置 短舱涡流片 设计准则 

分 类 号：V211.46[航空宇航科学与技术—航空宇航推进理论与工程] V224.5