仿生小片对翼型气动性能的影响分析

郝礼书; 张智昊; 杨博鉴; 许乐阳; 高永卫

doi:10.13224/j.cnki.jasp.20230782

仿生小片对翼型气动性能的影响分析

doi: 10.13224/j.cnki.jasp.20230782

郝礼书^{1, 2,},
张智昊^{1, 2},
杨博鉴¹,
许乐阳¹,
高永卫^{1, 2}

1.
西北工业大学航空学院，西安 710072
2.
飞行器基础布局全国重点实验室，西安 710072

基金项目: 国家自然科学基金（11502214）；翼型、叶栅空气动力学国家级重点实验室基金（D5150240010）

详细信息

作者简介:
郝礼书（1980-），男，副教授，博士，主要研究方向为流动控制。E-mail：haolishu@nwpu.edu.cn

中图分类号: V211.41⁺2
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出版历程
- 收稿日期: 2023-12-12
- 网络出版日期: 2025-08-13

Investigation on the effect of airfoil aerodynamic performance with bionic flap

HAO Lishu^{1, 2
,},
ZHANG Zhihao^{1, 2},
YANG Bojian¹,
XU Leyang¹,
GAO Yongwei^{1, 2}

1.
School of Aeronautics，Northwestern Polytechnical University，Xi’an 710072，China
2.
National Key Laboratory of Aircraft Configuration Design，Xi’an 710072，China

摘要

摘要:
针对自然界鸟类着陆时翅膀上表面羽毛轻微抬起的现象，以海鸥翼翅翼型为基础，在翼型上表面布置了一系列不同形状构型的小片，采用计算流体力学（CFD）的方法研究了仿生小片构型参数对翼型气动性能的影响。重点讨论了小片形状、小片间隙高度、小片角度及层叠状小片等参数对翼型气动力的影响，并通过流线、压力分布曲线、涡场等信息分析了仿生小片抑制流动分离的效果。研究结果表明：仿生小片在有限迎角范围内能改善翼型的失速特性，实现升力的增加和压差阻力的减小；小片角度及形状是影响翼型气动特性改善的关键因素，小片间隙高度及层叠状构型对分离流动的控制力则更弱一些；在所有11种小片构型中海鸥小片构型改善翼型失速特性的能力最强，其最大升力系数可以提高15.4%，改善翼型失速特性的有效迎角范围可达8°以上。上述研究结果也证实了鸟类着陆飞行时羽毛轻微抬起的气动原因，得到了改善翼型失速特性的关键参数，可以为后续仿生翼型的工程应用提供数据及理论支撑。
- 仿生小片 /
- 仿生翼型 /
- 失速特性 /
- 气动性能 /
- 计算流体力学
Abstract:
Considering the phenomenon that bird’s feathers on the wing are slightly raised when birds are landing, a series of small flaps with different configurations were arranged on the seagull bionic airfoil. The investigation on the effect of airfoil aerodynamic performance with bionic flap was studied by using computational fluid dynamics (CFD) method. The effects of flap shape, flap gap height, flap angle and laminated flap on the airfoil aerodynamic performance were discussed, and the effect of bionic flap on flow separation was analyzed by streamline, pressure distribution curve and vortex field. The results showed that the bionic flap can improve the stall characteristics of the airfoil within a limited range of angle of attack, leading to the increase of lift and the decrease of pressure drag. The angle and shape of the flaps were key factors to improve the aerodynamic characteristics of the airfoil, while the gap height of the flaps and the laminated configuration had weaker control over the separation flow. Among all the 11 flap configurations, seagull flap configuration had the strongest ability to improve the airfoil stall characteristics, its maximum lift coefficient can be increased by 15.4%, and the effective angle of attack range for improving the airfoil stall characteristics can reach more than 8°. The above research results also confirmed the aerodynamic reasons for raising feathers during the bird’s landing flight, and the key parameters to improve the stall characteristics of the airfoil were obtained, which can provide data and theoretical support for subsequent engineering application of the bionic airfoil.
- bionic flap /
- bionic airfoil /
- stall characteristics /
- aerodynamic performance /
- computational fluid dynamics

HTML

图 1 NPU-WA-180翼型升阻力特性计算验证

Figure 1. Numerical and validation of lift and drag coefficient of NPU-WA-180 airfoil

下载: 全尺寸图片幻灯片

图 2 仿生小片几何参数示意图

Figure 2. Schematic diagram of geometric parameters of bionic flap

下载: 全尺寸图片幻灯片

图 3 典型小片布局示意图

Figure 3. Diagram of the flap layout

下载: 全尺寸图片幻灯片

图 4 平板小片在翼型后缘不同角度时气动性能对比曲线

Figure 4. Comparison curve of airfoil aerodynamic performance of plane flap with different angles

下载: 全尺寸图片幻灯片

图 5 平板小片在不同角度时翼型绕流场对比（α=16°）

Figure 5. Comparison of airfoil flow fields of plane flap with different angles （α=16°）

下载: 全尺寸图片幻灯片

图 6 平板小片在不同间隙条件下的气动性能对比曲线

Figure 6. Comparison curve of aerodynamic performance of plane flap under different gap conditions

下载: 全尺寸图片幻灯片

图 7 小片不同外形时翼型气动性能的对比曲线

Figure 7. Comparison curve of aerodynamic performance of airfoil with different flap shapes

下载: 全尺寸图片幻灯片

图 8 翼型和不同形状的小片压力分布曲线对比（α =6°）

Figure 8. Comparison of pressure distribution curves of airfoil and flap with different shapes （α=6°）

下载: 全尺寸图片幻灯片

图 9 翼型和不同形状的小片压力分布曲线对比（α =16°）

Figure 9. Comparison of pressure distribution curves of airfoil and flap with different shapes （α=16°）

下载: 全尺寸图片幻灯片

图 10 海鸥小片在不同角度时翼型气动性能的对比

Figure 10. Comparison of airfoil aerodynamic performance of seagull flap with different angles

下载: 全尺寸图片幻灯片

图 11 海鸥翼型小片在不同倾斜角度时翼型涡场对比（α=16°）

Figure 11. Comparison of airfoil vortex field of seagull airfoil flap with different angles （α=16°）

下载: 全尺寸图片幻灯片

图 12 层叠小片对翼型气动性能影响的对比曲线

Figure 12. Comparison of aerodynamic performance of airfoil with combined seagull flaps

下载: 全尺寸图片幻灯片

图 13 不同小片构型的翼型涡场对比（α=20°）

Figure 13. Comparison of vortex field of airfoil with different flap configurations （α=20°）

下载: 全尺寸图片幻灯片

表 1 11种小片布局的几何参数信息

Table 1. Geometric parameter information of 11 kinds of flap layouts

序号	外形	间隙H	角度β/（°）	长度L	位置P
1	平板	0.0075c	0	0.4c	60%c
2	平板	0.0075c	5	0.4c	60%c
3	平板	0.0075c	10	0.4c	60%c
4	平板	0.0077c	10	0.4c	60%c
5	平板	0.008c	10	0.4c	60%c
6	NACA0008翼型	0.008c	10	0.4c	60%c
7	海鸥翼型	0.008c	10	0.4c	60%c
8	海鸥翼型	0.008c	5	0.4c	60%c
9	海鸥翼型	0.008c	0	0.4c	60%c
10	海鸥翼型	0.008c	0	0.2c	60%c
10	海鸥翼型	0.008c	0	0.2c	80%c
11	海鸥翼型	0.008c	0	0.3c	60%c
11	海鸥翼型	0.008c	0	0.2c	80%c

下载: 导出CSV

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