低雷诺数仿生分离流翼型气动特性初探

张庆; 薛榕融; 马浩统

doi:10.13224/j.cnki.jasp.20210154

低雷诺数仿生分离流翼型气动特性初探

doi: 10.13224/j.cnki.jasp.20210154

张庆^{1, 2,},
薛榕融^{3, 4,, ,},
马浩统^{3, 4}

1.
西安航空学院飞行器学院，西安 710077
2.
南洋理工大学机械与航空工程学院，新加坡 639798
3.
中国科学院光电技术研究所，成都 610209
4.
中国科学院光束控制重点实验室，成都 610209

基金项目:

四川省海内外高层次人才“千人计划” A18S001

国家自然科学基金面上项目 62175243

详细信息

作者简介:
张庆（1987-），男，讲师，博士，主要研究方向为仿生飞行器。E⁃mail：zhangqing2220@mail.nwpu.edu.cn

通讯作者:
薛榕融（1990-），男，助理研究员，博士，主要研究方向为飞行力学。E⁃mail：xuerongrong@ioe.ac.cn

中图分类号: V211.41⁺2
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- 文章访问数: 80
- HTML浏览量: 19
- PDF量: 30
- 被引次数: 0
出版历程
- 收稿日期: 2021-04-07

Preliminary aerodynamic exploration for bioinspired separated flow airfoil at low Reynolds number

ZHANG Qing^{1, 2
,},
XUE Rongrong^{3, 4,
, ,},
MA Haotong^{3, 4}

1.
School of Aircraft，Xi'an Aeronautical University，Xi'an 710077，China
2.
School of Mechanical and Aerospace Engineering，Nanyang Technological University，Singapore 639798
3.
Institute of Optics and Electronics，Chinese Academy of Sciences，Chengdu 610209，China
4.
Key Laboratory of Optical Engineering，Chinese Academy of Sciences，Chengdu 610209，China

摘要

摘要:
为了探索适合低雷诺数微型飞行器的翼型形式，基于对自然界鸟类和昆虫滑翔飞行时翅膀形状的观察，设计出一种由前缘削尖平板和后缘圆弧翼型组合而成的仿生分离流翼型。数值研究结果表明，气流在削尖平板的前缘点强制分离，形成大范围低压分离流动，随后在后部圆弧翼上表面再附形成稳定低压涡流区，从而实现较高的气动效率和较强的抵抗大气湍流的能力。上削尖平板可以使流动分离点固定在削尖点。相对于单独平板，仿生分离流翼型的升力系数有大幅提高，迎角为4°时提高了112%。此外，仿生分离流翼型可以在较宽的迎角范围内（4°~20°）保持高升力，但是迎角增加，阻力也快速增大，因此小迎角情况下（小于4°）气动效率更优。
- 仿生分离流翼型 /
- 低雷诺数流动 /
- 流动分离 /
- 气动特性 /
- 大气湍流
Abstract:
In order to explore the type of airfoil suitable for low Reynolds number micro aerial vehicles，based on the observation of the wing shape of natural birds and insects during gliding flight in nature，a bioinspired separated flow airfoil composed of a sharpened leading edge flat plate and a circular arc airfoil was designed.Computational results demonstrated that the flow was forced to be separated at the sharp leading edge to generate low pressure flow and then be reattached at the upper surface of the rear arc airfoil to form stable low pressure vortical flow，thus high aerodynamic efficiency and strong turbulence resistance could be achieved.The separation could be fixed at the sharp leading edge point for upper⁃cropped flat plate.Compared with the single cropped flat plate，the lift coefficient of the bioinspired separated flow airfoil was improved significantly，by 112% at angle of attack 4°.In addition，the bioinspired separated flow airfoil can maintain high lift within a wide range of angle of attack between 4° and 20°，but the aerodynamic efficiency was higher at angles of attack lower than 4° because the drag increased rapidly with the increase of the angle of attack.
- bioinspired separated flow airfoil /
- low Reynolds number flow /
- flow separation /
- aerodynamic performance /
- aerodynamic turbulence
注释:

1) 陈越

HTML

下载: 全尺寸图片幻灯片

图 8 不同迎角下三种翼型表面的压力系数分布对比

Figure 8. Comparison of wall pressure coefficient of three airfoils at different angles of attack

下载: 全尺寸图片幻灯片

表 1 不同方法计算的升力系数阻力系数对比

Table 1. Comparison of lift and drag coefficients by different computational methods

计算方法	升力系数（相对误差）	阻力系数（相对误差）
实验值	0.561（参考值）	0.021（参考值）
无黏模型	0.654 1（16.60%）	0.002 5（-88.10%）
S⁃A模型	0.556 1（-0.87%）	0.021 9（4.29%）
SST κ⁃ω模型	0.548 1（-2.30%）	0.020 5（-2.38%）
$γ ⁃ R e_{θ}$ 转捩模型	0.565 4（0.78%）	0.022 3（6.19%）

下载: 导出CSV

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