[1]王仁华,张海黎,黄同高,等.扇翼飞行器绕翼型流动数值研究[J].应用科技,2011,38(12):5-8.[doi:1009- 671X(2011)12- 0005- 05]
 WANG Renhua,ZHANG Haili,HUANG Tonggao,et al.Numerical study of flow over fan-wing airfoil[J].Applied science and technology,2011,38(12):5-8.[doi:1009- 671X(2011)12- 0005- 05]
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扇翼飞行器绕翼型流动数值研究(/HTML)
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《应用科技》[ISSN:1009-671X/CN:23-1191/U]

卷:
第38卷
期数:
2011年12期
页码:
5-8
栏目:
自动化技术
出版日期:
2011-12-05

文章信息/Info

Title:
Numerical study of flow over fan-wing airfoil
文章编号:
1009- 671X(2011)12- 0005- 05
作者:
王仁华1张海黎2黄同高1梁焜1杨忠1
(1.南京航空航天大学 自动化学院,江苏 南京210016; 2.中国人民解放军 驻南京地区军事代表室,江苏 南京210016)
Author(s):
WANG Renhua1ZHANG Haili2 HUANG Tonggao1LIANG Kun1YANG Zhong1
(1.College of Automation Engineering, Nanjing University of Aeronautics & Astronautics, Nanjing 210016, China; 2. Military Representative Office of Nanjing, PLA, Nanjing 210016, China)
关键词:
扇翼飞行器数值模拟滑移网格横流式风扇翼型前缘高度
Keywords:
fan-wing aircraft numerical simulation sliding mesh
分类号:
V211.3;V221+.3
DOI:
1009- 671X(2011)12- 0005- 05
文献标志码:
A
摘要:
扇翼飞行器以其低速大载荷、低噪音特性在军用及民用领域有着广泛的应用前景.基于CFD软件采用滑移网格技术对简化为二维的绕翼型流动进行数值模拟,得到低速大迎角下绕翼型的流场,分析并比较了不同迎角下的流场结构,给出了升阻力随迎角的变化关系.在此基础上通过比对分析翼型局部几何形状改变后得到的数值模拟结果,得到了飞行器机翼前缘高度对绕翼型流场的影响以及相应的升阻力变化情况,并讨论了引起这些影响和变化的可能原因.最终给出可用于扇翼飞行器设计的方案.
Abstract:
The fan-wing aircraft has a wide application prospect in military and civilian fields due to its characteristics of low speed, large load capacity, and low noise. Using the sliding mesh technology based on computational fluid dynamics (CFD), the flow over the two-dimensional airfoil is simulated, under the condition of low-speed and high angle of attack. The flow features at different angles of attack are analyzed and compared, and the variation of lift and drag changing with the angle of attack is acquired. And on this basis, a numerical simulation was made on the fan-win which was modified locally in geometry. With the analysis and comparison, the effect of fan-wing leading edge height on the flow field around the airfoil is acquired, as well as the corresponding changes in lift and drag. The possible reasons for such a significant effect are discussed. This paper is valuable for those working in the area of high-lift wing design.

参考文献/References:

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[3]DUDDEMPUDI D, YAO Yufeng, EDMONDSON D, et al. Computational study of flow over generic fan-wing airfoil[J]. Aircraft Engineering and Aerospace Technology, 2007(3): 238- 244.
[4]ASKARI S, SHOJAEEFARD M H. Shape optimization of the airfoil comprising a cross flow fan[J]. Aircraft Engineering and Aerospace Technology, 2009(5): 407-415.
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备注/Memo

备注/Memo:
基金项目:国家自然科学基金资助项目(60674100);高等学校博士学科点专项科研基金资助项目(20113218110013).
作者简介:王仁华(1984-),男,硕士研究生,主要研究方向:导航、制导和控制,E-mail:BlueM446@163.com.
更新日期/Last Update: 2012-02-29