论文:2013,Vol:31,Issue(4):522-529
引用本文:
白俊强, 刘南, 邱亚松, 陈迎春, 李亚林, 周涛. 大型民用运输机短舱涡流片增升效率以及参数影响研究[J]. 西北工业大学
Bai Junqiang, Liu Nan, Qiu Yasong, Chen Yinchun, Li Yalin, Zhou Tao. Investigation on Influence of Nacelle Chine of Large Civil Transport Aircraft on High-Lift Efficiency and on Influence of Relevant Parameters[J]. Northwestern polytechnical university

大型民用运输机短舱涡流片增升效率以及参数影响研究
白俊强1, 刘南1, 邱亚松1, 陈迎春2, 李亚林2, 周涛2
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
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。
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   
Investigation on Influence of Nacelle Chine of Large Civil Transport Aircraft on High-Lift Efficiency and on Influence of Relevant Parameters
Bai Junqiang1, Liu Nan1, Qiu Yasong1, Chen Yinchun2, Li Yalin2, Zhou Tao2
1. College of Aeronautics, Northwestern Polytechnial University, Xi'an, 710072, China;
2. Shanghai Aircraft Design Institute, Shanghai 200232, China
Abstract:
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.
Key words:    computational fluid dynamics    transport aircraft    flow fields    vortex flow    high lift    nacelle chine    design rules   
收稿日期: 2012-10-23     修回日期:
DOI:
通讯作者:     Email:
作者简介: 白俊强(1971-),西北工业大学教授,主要从事飞机气动设计和计算流体力学的研究。
相关功能
PDF(983KB) Free
打印本文
把本文推荐给朋友
作者相关文章
白俊强  在本刊中的所有文章
刘南  在本刊中的所有文章
邱亚松  在本刊中的所有文章
陈迎春  在本刊中的所有文章
李亚林  在本刊中的所有文章
周涛  在本刊中的所有文章

参考文献:
[1] 邱亚松, 白俊强, 黄 琳等.翼吊发动机短舱对三维增升装置的影响及改善措施研究.空气动力学学报, 2012, 1: 7-13 Qiu Y S, Bai J Q, Huang L, et.al.Study about Influence of Wing-Mounted Engine Nacelle on High-Lift System and Improvement Measures.Acta Aerodynamica Sinica, 2012, 1: 7-13 (in Chinese)
[2] Rudnik R.Stall behavior of the Eurolift High Lift Configurations.AIAA-2008-836
[3] Kanazaki M, et.al.Efficient Design Exploration on Nacelle Chine Installation Using Kriging Model in Wing Tunnel Testing.AIAA-2008-155
[4] Ito Y, M urayama M, Yamamoto K, et.al.Efficient Computational Fluid Dynamics Evaluation of Small-Device Locations with Automatic Local Remeshing.AIAA Journal, 2009, 47(5): 1270-1276
[5] Yokokawa Y, Kanazaki M, Murayama M.Investigation of the Flow Over Nacelle /Pylon and Wing Controlled with a Vortex Generator in High-Lift Configuration.26th International Congress of the Aeronautical Sciences, 2008
[6] Visser K D, Ferrero M C F, Nelson R C.Physical Considerations of Leading Edge Flows.AIAA-2004-5083
相关文献:
1.白俊强, 辛亮, 刘南, 华俊, 董建鸿, 雷武涛, 张晓亮.分布式零质量射流控制增升装置分离的数值模拟[J]. 西北工业大学, 2014,32(2): 188-194
2.孟祥尧, 邱志明, 张鹏, 宋保维.水中化学羽流的建模和数值模拟分析[J]. 西北工业大学, 2014,32(5): 775-780
3.王刚, 曾铮, 叶正寅.混合非结构网格下壁面最短距离的快速计算方法[J]. 西北工业大学, 2014,32(4): 511-516
4.胡斌, 潘光, 杜晓旭, 黄桥高, 王一云.基于分块网格技术的潜艇粘性绕流场数值计算研究[J]. 西北工业大学, 2012,30(5): 689-693
5.郭东, 徐敏, 陈士橹.基于网格速度法的非定常流场模拟和动导数计算[J]. 西北工业大学, 2012,30(5): 784-788