吉林大学学报(工学版) ›› 2014, Vol. 44 ›› Issue (2): 387-391.doi: 10.13229/j.cnki.jdxbgxb201402017

• 论文 • 上一篇    下一篇

仿生缝翼的增升作用

葛长江1, 葛美辰2, 梁平1, 张志辉1, 任露泉1   

  1. 1. 吉林大学 工程仿生教育部重点实验室, 长春 130022;
    2. 吉林大学 机械科学与工程学院 长春 130022
  • 收稿日期:2013-03-15 出版日期:2014-02-01 发布日期:2014-02-01
  • 通讯作者: 任露泉（1944- ），男，教授，博士生导师，中国科学院院士.研究方向：工程仿生.E-mail：lqren@jlu.edu.cn E-mail:lqren@jlu.edu.cn
  • 作者简介:葛长江（1981- ），男，博士.研究方向：工程仿生.E-mail：163_gongbo@163.com
  • 基金资助:

    国家自然科学基金项目（31071928）.

High-lift effect of bionic slat

GE Chang-jiang1, GE Mei-chen2, LIANG Ping1, ZHANG Zhi-hui1, REN Lu-quan1   

  1. 1. Key Laboratory of Bionic Engineering of Ministry of Education, Jilin University, Changchun 130022, China;
    2. College of Mechanical Science and Engineering, Jilin University, Changchun 130022, China
  • Received:2013-03-15 Online:2014-02-01 Published:2014-02-01

RICH HTML

0   

PDF (PC)

544

摘要：

以长耳鸮的翅膀为模本构建仿生翼型，并在此基础上构建没有凹口的仿生缝翼及仿生多段翼型。利用快速成型系统制作相应的准二维试验模型，并在低湍流度的风洞内进行试验，结果显示：在攻角小于5°时，仿生翼型的升力系数更大，而在攻角大于5°时，具有仿生缝翼的仿生多段翼型的升力系数更优。同时，仿生多段翼型中仿生缝翼能提高失速角和最大升力系数，而且还能延迟升力系数曲线斜率的下降，从而在一定攻角范围内阻止前缘分离的发生。在低雷诺数下的绕翼烟线显示了仿生翼型的前缘分离，但在相同工况下的仿生多段翼型的流场中没有出现前缘分离。这个优点也许可以被用在未来的前缘缝翼的设计中。

关键词: 工程仿生学, 小翼羽, 仿生缝翼, 风洞, 增升作用

Abstract:

In this paper, a bionic airfoil mimicking the wing of a long-eared owl is proposed. On this basis, a bionic slat without cove and multi-element airfoil is built. In order to reveal high-lift effect of the bionic slat, the corresponding quasi-two-dimensional models are manufactured by rapid manufacturing and prototyping system. Experiments are conducted in a low-turbulence wind tunnel. The results show that the lift coefficient of the bionic airfoil is larger when the angle of attack is less than 5°, but lift coefficient of the bionic multi-element airfoil with slat is larger s when the angle of attack is greater than 5°. The bionic slat can increase the stall angle and the maximum lift coefficient; at the same time, it can also delay the decline of the lift coefficient curve slope in order to prevent the leading-edge separation within a certain range of angle of attack. Furthermore, the flow field around the models is visualized by smoke wire method, which shows the leading-edge separation of the bionic airfoil at low Reynolds numbers. However, the finding does not occur in the flow field of the bionic multi-element airfoil at the same conditions. This superiority may be used as reference in the design of the leading-edge slat or slot.

Key words: engineering bionics, alula, bionic slat, wind tunnel, high-lift effect

中图分类号: 

  • TB17

[1] Soderman P T, Kafyeke F, Boudreau J, et al. Airframe noise study of a Bombardier CRJ-700 aircraft model in the NASA Ames 7-by 10-foot wind tunnel[J]. International Journal of Aeroacoustics, 2004, 3(1): 1-42.

[2] Chow L C, Mau K, Remy H. Landing gear and high lift devices airframe noise research[C]//AIAA Paper, 2002-2408.

[3] Zhaokai Ma. Slat noise attenuation using acoustic liner[C]//AIAA Paper, 2005-3009.

[4] Smith M G, Chow L C, Molin N. Attenuation of slat trailing edge noise using slat gap acoustic liners[C]//AIAA Paper, 2006-2666.

[5] Choudhari M, Khorrami M R, Lockard D P. Slat cove noise modeling: a posteriori analysis of unsteady RANS simulations[C]//AIAA Paper, 2002 -2468.

[6] Takeda K, Ashcroft G B, Zhang X. Unsteady aerodynamics of slat Cove flow in a high-lift device configuration[C]//AIAA Paper, 2001-0706.

[7] 徐成宇, 钱志辉, 刘庆萍, 等. 基于长耳鸮翼前缘的仿生耦合翼型气动性能[J].吉林大学学报: 工学版, 2010, 40 (1): 108-112. Xu Cheng-yu, Qian Zhi-hui, Liu Qing-ping, et al. Aerodynamic performance of bionic coupled foils based on leading edge of long-eared owl wing[J]. Journal of Jilin University (Engineering and Technology Edition), 2010, 40 (1): 108-112.

[8] Meseguer J, Franchini S, Perez-Grande I, et al. On the aerodynamics of leading-edge high-lift devices of avian wings[J]. Proc Inst Mech Eng G, 2005, 219: 63-68.

[9] van Der Burg J W, Eliasson P, Delille T, et al. Geometric installation and deformation effects in high-lift flows[C]//AIAA Journal, 2009, 47: 60-70.

[10] Rudnik R. Stall behaviour of the eurolift high-lift configurations[C]//AIAA Paper, 2008-836.

[11] Graham R R. The silent flight of owls[J]. J Roy Aero Soc, 1934, 38: 837-843.

[12] Lilley G M. A study of the silent flight of the owl[C]//AIAA Paper, 1998-2340.

[13] Nachtigall W, Kempf B. Vergleichende untersuchungen zur flugbiologischen funktion des daumenfittichs (Alula spuria) bei vgeln[J]. Z vergl Physiologie, 1971, 71: 326-341.

[14] Liu T S, Kuykendoll K, Rhew R, et al. Avian Wing Geometry and Kinematics[C]//AIAA Journal, 2006, 44: 954-963.

[15] Klan S, Bachmann T, Klaas M, et al. Experimental analysis of the flow field over a novel owl based airfoil[J]. Exp Fluids, 2009, 46: 975-989.
[1] 熙鹏,丛茜,王庆波,郭华曦. 仿生条纹形磨辊磨损试验及耐磨机理分析[J]. 吉林大学学报(工学版), 2018, 48(6): 1787-1792.
[2] 郭昊添,徐涛,梁逍,于征磊,刘欢,马龙. 仿鲨鳃扰流结构的过渡段换热表面优化设计[J]. 吉林大学学报(工学版), 2018, 48(6): 1793-1798.
[3] 田为军, 王骥月, 李明, 张兴旺, 张勇, 丛茜. 面向水上机器人的水黾运动观测[J]. 吉林大学学报(工学版), 2018, 48(3): 812-820.
[4] 钱志辉, 周亮, 任雷, 任露泉. 具有仿生距下关节和跖趾关节的完全被动步行机[J]. 吉林大学学报(工学版), 2018, 48(1): 205-211.
[5] 王宏朝, 单希壮, 杨志刚. 地面效应模拟对环境风洞中车辆冷却系统试验影响的数值模拟[J]. 吉林大学学报(工学版), 2017, 47(5): 1373-1378.
[6] 田丽梅, 王养俊, 李子源, 商延赓. 仿生功能表面内流减阻测试系统的研制[J]. 吉林大学学报(工学版), 2017, 47(4): 1179-1184.
[7] 陈东辉, 刘伟, 吕建华, 常志勇, 吴婷, 慕海锋. 基于虾夷扇贝体表结构的玉米茬根捡拾器仿生设计[J]. 吉林大学学报(工学版), 2017, 47(4): 1185-1193.
[8] 王颖, 李建桥, 张广权, 黄晗, 邹猛. 基于多种介质的仿生步行足力学特性[J]. 吉林大学学报(工学版), 2017, 47(2): 546-551.
[9] 葛长江, 叶辉, 胡兴军, 于征磊. 鸮翼后缘噪声的预测及控制[J]. 吉林大学学报(工学版), 2016, 46(6): 1981-1986.
[10] 李梦, 苏义脑, 孙友宏, 高科. 高胎体仿生异型齿孕镶金刚石钻头[J]. 吉林大学学报(工学版), 2016, 46(5): 1540-1545.
[11] 梁云虹, 任露泉. 自然生境及其仿生学初探[J]. 吉林大学学报(工学版), 2016, 46(5): 1746-1756.
[12] 梁云虹, 任露泉. 人类生活及其仿生学初探[J]. 吉林大学学报(工学版), 2016, 46(4): 1373-1384.
[13] 张钦国, 秦四成, 杨立光, 马润达, 刘宇飞, 李武. 基于虚拟风洞的装载机动力舱热环境预测分析[J]. 吉林大学学报(工学版), 2016, 46(1): 50-56.
[14] 钱志辉， 苗怀彬， 任雷， 任露泉. 基于多种步态的德国牧羊犬下肢关节角[J]. 吉林大学学报(工学版), 2015, 45(6): 1857-1862.
[15] 邹猛， 于用军， 张荣荣， 魏灿刚， 王会霞. 仿牛角结构薄壁管吸能特性仿真分析[J]. 吉林大学学报(工学版), 2015, 45(6): 1863-1868.
Viewed
Full text


Abstract

Cited
  Shared   
  Discussed   
No Suggested Reading articles found!
版权所有 © 《吉林大学学报(工学版)》编辑部
地址：长春市人民大街5988号　电话：+86-431-85095297　传真：+86-431-85094074　E-mail: xbgxb@jlu.edu.cn
本系统由北京玛格泰克科技发展有限公司设计开发