柔性扑翼翼型的气动性能仿真分析

王奇; 朱寅鑫; 牛培行; 刘少宝

doi:10.21656/1000-0887.430155

柔性扑翼翼型的气动性能仿真分析

doi: 10.21656/1000-0887.430155

王奇^{1, 2,},
朱寅鑫^{1, 2},
牛培行^{1, 2},
刘少宝^{1, 2, ,}

1.
南京航空航天大学航空学院机械结构力学及控制国家重点实验室，南京 210016
2.
南京航空航天大学航空学院多功能轻量化材料与结构工信部重点实验室，南京 210016

基金项目: 国家自然科学基金（11902155）；江苏省自然科学基金（BK20190382）；江苏高校优势学科建设工程项目

详细信息

作者简介:
王奇（1998—），男，硕士生（E-mail：2902930121@qq.com）

刘少宝（1988—），男，副研究员，博士，硕士生导师（通讯作者. E-mail：sbliu@nuaa.edu.cn）

中图分类号: O355; V211.3
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- 文章访问数: 1057
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- 被引次数: 0
出版历程
- 收稿日期: 2022-05-05
- 修回日期: 2022-05-16
- 网络出版日期: 2022-05-26
- 刊出日期: 2022-05-01

Simulation of Aerodynamic Performances of Flexible Flapping Wing Airfoils

WANG Qi^{1, 2
,},
ZHU Yinxin^{1, 2},
NIU Peixing^{1, 2},
LIU Shaobao^{1, 2
, ,}

1.
State Key Laboratory of Mechanics and Control of Mechanical Structures, College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, P.R.China
2.
MIIT Key Laboratory of Multifunctional Lightweight Materials and Structures, College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 21006, P.R.China

摘要

摘要:
与固定翼相比，在低速、小Reynolds数条件下，扑翼飞行具有显著的气动性能优势，受到越来越多的重视。然而，目前对扑翼翼型的研究以刚性翼型为主，对柔性翼型气动性能认识还不清楚。该文建立了柔性椭圆翼型的流固耦合仿真模型，分析了不同风速、迎角下柔性椭圆翼型的周围流场、变形以及气动性能。仿真结果表明，较刚性翼型，柔性翼型延缓了尾涡脱落时间，有效降低升力扰动振荡频率；柔性翼型显著抑制了尾流流场的扰动，降低升力扰动振荡幅值，合适的弹性模量翼型使得扰动振荡完全消除。研究结果可为软飞行器气动设计提供参考。
- 柔性翼型 /
- 流固耦合 /
- 气动性能 /
- 升力 /
- 有限元
Abstract:
Compared with fixed wings, the flapping wing has a significant aerodynamic performance advantage at low speeds and low Reynolds numbers, which draws more and more attentions. But most previous studies focus on rigid flapping airfoils, the aerodynamic performances of flexible flapping airfoils are still unclear. A fluid-solid coupling model for the flexible elliptical airfoils was developed to analyze the flow field around the airfoil, the airfoil deformation and the aerodynamic characteristics of airfoils, at different wind speeds and attack angles. Compared with the rigid airfoil, the flexible airfoil can delay the shedding time of the wake vortex and reduce the oscillation frequency of the disturbance on the lift force. The flexible airfoil significantly suppresses the disturbance of the wake flow and reduces the oscillation amplitude of disturbance. Even, the airfoil disturbance oscillation can be completely eliminated at an appropriate Young’s modulus of the airfoil. These results provide a theoretical guidance for the design of soft aircraft.
- flexible airfoil /
- fluid-solid coupling /
- aerodynamic performance /
- lift force /
- finite element

HTML全文

图 1 椭圆翼型几何模型：（a）流体域几何尺寸；（b）椭圆翼型几何尺寸

Figure 1. The geometric model for the elliptical airfoil: (a) geometric sizes of the fluid domain; (b) geometric sizes of the elliptical airfoil

下载: 全尺寸图片幻灯片

图 2 流体网格划分：（a）整体网格划分；（b）壁面附近网格加密处理

Figure 2. Meshing of the fluid domain: (a) meshing of the whole model; (b) mesh refinement near the wall

下载: 全尺寸图片幻灯片

图 3 刚性翼型流场流速分布：（a）速度云图；（b）压力云图

注　为了解释图中的颜色，读者可以参考本文的电子网页版本，后同。

Figure 3. Characteristics of the flow field around the rigid airfoil: (a) the velocity contour; (b) the pressure contour

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图 4 刚性翼型升力与Pesavento和Wang^[10]的数值计算结果对比

Figure 4. Comparison of lift forces of the rigid airfoil to the numerical results of Pesavento and Wang^[10]

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图 5 不同迎角下的刚性翼型流场速度云图

Figure 5. Velocity contours of the flow field around the rigid airfoil at different attack angles

下载: 全尺寸图片幻灯片

图 6 不同迎角下的刚性翼型流场压力云图

Figure 6. Pressure contours of the flow field around the rigid airfoil at different attack angles

下载: 全尺寸图片幻灯片

图 7 不同风速下刚性翼型的升力、阻力及升阻比：（a）升力；（b）阻力；（c）升阻比

Figure 7. Lift forces, drag forces and lift-drag ratios of the rigid airfoil at different wind speeds: (a) lift forces; (b) drag forces; (c) lift-drag ratios

下载: 全尺寸图片幻灯片

图 8 柔性椭圆翼型有限元模型：（a）网格划分；（b）流固耦合面与固定面

Figure 8. The finite element model for the flexible elliptical airfoil: (a) the meshing; (b) the fluid-solid coupling and the fixed surface

下载: 全尺寸图片幻灯片

图 9 不同弹性模量的柔性翼型流场速度云图

Figure 9. Velocity contours of the flow field around the flexile airfoil with different Young’s moduli

下载: 全尺寸图片幻灯片

图 10 不同弹性模量的柔性翼型流场压力云图

Figure 10. Pressure contours of the flow field around the flexile airfoil with different Young’s moduli

下载: 全尺寸图片幻灯片

图 11 不同弹性模量的柔性翼型位移云图

Figure 11. Deformation contours of the flexile airfoil with different Young’s moduli

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图 12 柔性翼型的升力和阻力：（a）升力；（b）阻力

Figure 12. Lift forces and drag forces of the flexible airfoil: (a) lift forces; (b) drag forces

下载: 全尺寸图片幻灯片

图 13 不同迎角下的刚性翼型（左）与柔性翼型（右）的周围流场

Figure 13. Velocity contours of the fluid field around the rigid (left) and the flexible (right) airfoil with different attack angles

下载: 全尺寸图片幻灯片

图 14 柔性翼型的升力、阻力及升阻比随迎角变化：（a）升力；（b）阻力；（c）升阻比

Figure 14. Lift forces, drag forces and lift-drag ratios of the flexible airfoil vs. the attack angle: (a) lift forces; (b) drag forces; (c) lift-drag ratios

下载: 全尺寸图片幻灯片

参考文献(12)

[1]	孙茂, 吴江浩. 昆虫飞行的高升力机理和能耗[J]. 北京航空航天大学学报, 2003, 29(11): 970-977. (SUN Mao, WU Jianghao. Unsteady lift mechanisms and energetic in flying insects[J]. Journal of Beijing University of Aeronautics and Astronautics, 2003, 29(11): 970-977.(in Chinese) doi: 10.3969/j.issn.1001-5965.2003.11.004
[2]	ELLINGTON C P, BERG C V D, WILLMOTT A P, et al. Leading-edge vortices in insect flight[J]. Nature, 1996, 384(6610): 626-630. doi: 10.1038/384626a0
[3]	DICKINSON M H, LEHMANN F O, SANE S P. Wing rotation and the aerodynamic basis of insect flight[J]. Science, 1999, 284(5422): 1954-1960. doi: 10.1126/science.284.5422.1954
[4]	TANG J, VIIERU D, SHYY W. A study of aerodynamics of low Reynolds number flexible airfoils[C]//37th AIAA Fluid Dynamics Conference and Exhibit. Miami, USA, 2007.
[5]	VISBAL M R, GORDNIER R E, GALBRAITH M C. High-fidelity simulations of moving and flexible airfoils at low Reynolds numbers[J]. Experiments in Fluids, 2009, 46(5): 903-922. doi: 10.1007/s00348-009-0635-4
[6]	张兴伟, 周超英, 谢鹏. 扑翼柔性变形对悬停气动特性影响的数值研究[J]. 哈尔滨工业大学学报, 2012, 44(1): 115-119. ZHANG Xingwei, ZHOU Chaoying, XIE Peng. Numerical study on the effect of flapping wing deformation on aerodynamic performance in hovering flight[J]. Journal of Harbin Institute of Technology, 2012, 44(1): 115-119. (in Chinese)
[7]	王姝歆, 周建华, 颜景平. 微小型仿生飞行机器人柔性翅的仿生设计与实验研究[J]. 实验流体力学, 2006, 20(1): 75-79. (WANG Shuxin, ZHOU Jianhua, YAN Jingping. Bionic design and experiment on flexible wings of a bionic flying micro-robot[J]. Journal of Experiments in Fluid Mechanics, 2006, 20(1): 75-79.(in Chinese) doi: 10.3969/j.issn.1672-9897.2006.01.018
[8]	KANG W, ZHANG J Z, LEI P F, et al. Computation of unsteady viscous flow around a locally flexible airfoil at low Reynolds number[J]. Journal of Fluids and Structures, 2014, 46: 42-58. doi: 10.1016/j.jfluidstructs.2013.12.010
[9]	陶真新, 李绍斌, 宋西镇. 低雷诺数下柔性翼型气动性能分析[J]. 力学与实践, 2017, 39(2): 145-151. TAO Zhenxin, LI Shaobin, SONG Xizhen. The aerodynamic performance of a flexible airfoil at low Reynolds number[J]. Mechanics in Engineering, 2017, 39(2): 145-151. (in Chinese)
[10]	PESAVENTO U, WANG Z J. Flapping wing flight can save aerodynamic power compared to steady flight[J]. Physical Review Letter, 2009, 103(11): 118102. doi: 10.1103/PhysRevLett.103.118102
[11]	杨金广, 吴虎. 双方程k-ω SST湍流模型的显式耦合求解及其在叶轮机械中的应用[J]. 航空学报, 2014, 35(1): 116-124. (YANG Jinguang, WU Hu. Explicit coupled solution of two-equation k-ω SST turbulence model and its application in turbomachinery flow simulation[J]. Acta Aeronautica et Astronautica Sinica, 2014, 35(1): 116-124.(in Chinese)
[12]	MENTER F R. Zonal two equation k-ω turbulence models for aerodynamic flows[C]//AIAA 23rd Fluid Dynamics, Plasmadynamics, and Leaders Conference. Orlando, USA, 1993.