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

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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

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