Numerical study of high performance on the influence of angle of attack on aerodynamic performance of wing flapping

ZHU Xianqi; SUN Xiangcheng; WANG Xian

doi:10.7638/kqdlxxb-2021.0038

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Numerical study of high performance on the influence of angle of attack on aerodynamic performance of wing flapping

更新时间：2026-05-28

- Numerical study of high performance on the influence of angle of attack on aerodynamic performance of wing flapping
- Vol. 40, Issue 5, Pages: 50-60(2022)
- 作者机构：
  
  1. 西安交通大学航天航空学院，机械结构强度与振动国家重点实验室,西安,710049
  2. 陕西省先进飞行器服役环境与控制重点实验室,西安,710049
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2021.0038
  CLC： V276
- Published：2022
- 稿件说明：
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祝衔琦, 孙祥程, 王娴. 迎角对扑翼运动气动性能影响的高性能数值研究[J]. 空气动力学学报, 2022, 40(5): 50−60.

ZHU Xianqi, SUN Xiangcheng, WANG Xian. Numerical study of high performance on the influence of angle of attack on aerodynamic performance of wing flapping[J]. 2022, 40(5): 50-60.
祝衔琦, 孙祥程, 王娴. 迎角对扑翼运动气动性能影响的高性能数值研究[J]. 空气动力学学报, 2022, 40(5): 50−60. DOI： 10.7638/kqdlxxb-2021.0038

ZHU Xianqi, SUN Xiangcheng, WANG Xian. Numerical study of high performance on the influence of angle of attack on aerodynamic performance of wing flapping[J]. 2022, 40(5): 50-60. DOI： 10.7638/kqdlxxb-2021.0038.

摘要

为了设计更高效、高机动性的扑翼飞行器，需要对扑翼运动机理进行细致的动力学研究。其中，迎角是影响扑翼运动气动性能的关键因素。本文结合格子Boltzmann法与Level-Set动边界识别法，建立了含有动边界的流场模拟方法，并采用GPU加速，数值研究了迎角对扑翼运动气动性能的影响。结果表明：增大迎角，扑翼运动的升阻比呈现先增大后减小的趋势，当迎角

= 10°时，能够获得最佳气动性能。

= 0°～40°范围内，随着迎角的增大，扑翼翼尖处的上下翼面压差比翼根、翼中处大，在翼尖处提供了更大的升力。随着迎角的增大，扑翼的前缘涡附着于翼面的面积明显增大，扑翼后方脱落的涡旋也较难耗散，提高了扑翼的升力；同时，翼尖涡的强度和影响范围变大，增加了扑翼的阻力。

Abstract

In order to design a more efficient and highly maneuverable flapping-wing aircraft

it is necessary to conduct meticulous aerodynamics research on the flapping-wing motion mechanism. The angle of attack is a key factor affecting the aerodynamic performance of a flapping-wing motion. Based on the Lattice Boltzmann method and the Level-Set moving boundary recognition method with the GPU acceleration

this work carries out the aerodynamic performance of flapping-wing with the angle of attack (

$ \theta $

img text_id='M3' class='formula-img' style='display:none;' src='2021-038_M3.jpg'>

) from 0° to 60°. The results show that with increasing of

$ \theta $

img text_id='M3' class='formula-img' style='display:none;' src='2021-038_M3.jpg'>

the lift-to-drag ratio of the flapping-wing increases and then decreases. When

$ \theta =10^{ \circ } $

img text_id='M5' class='formula-img' style='display:none;' src='2021-038_M5.jpg'>

flapping-wing exhibits the best aerodynamic performance. In the range of

$\theta =0^{ \circ } \sim 40^{ \circ }$

img text_id='M6' class='formula-img' style='display:none;' src='2021-038_M6.jpg'>

with increasing of

$ \theta $

img text_id='M3' class='formula-img' style='display:none;' src='2021-038_M3.jpg'>

the pressure difference between the upper and lower wing surfaces at the tip of the flapping-wing is greater than that at the root and middle of the wing

which provide greater lift force at the wing tip. As the

$ \theta $

img text_id='M3' class='formula-img' style='display:none;' src='2021-038_M3.jpg'>

increasing

the area where the leading edge vortex attaches to the wing surface increases

and the vortices that fall off behind the flapping-wing are also difficult to dissipate

which lead to the increasing of the lift force of the flapping-wing. At the same time

the strength and range of influence of the wingtip vortex become larger

which lead to the increasing of the drag force of the flapping-wing.

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references

XIAO T H, LUO D M, ZHENG X M, et al. Progress and challenges in unsteady aerodynamic optimization design of bionic flapping-wings[J]. Acta Aerodynamica Sinica, 2018, 36(1): 80-87. (in Chinese)

NING Q, BAI C R, WU J, et al. Investigation of flapping-wing MAV in wind tunnel[J]. Science Technology and Engineering, 2007, 7(16): 4239-4241. (in Chinese)

BAO F, YANG Q, HE Y. Experimental investigation on shedding vortex and lift mechanism of flapping wing model with single degree of freedom[J]. Journal of Aerospace Power, 2014, 29(5): 1091-1098. (in Chinese)

ENNOS A R. The kinematics and aerodynamics of the free flight of some Diptera[J]. Journal of Experimental Biology, 1989, 142(1): 49-85. DOI: 10.1242/jeb.142.1.49

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

LIU H, KAWACHI K. A numerical study of insect flight[J]. Journal of Computational Physics, 1998, 146(1): 124-156. DOI: 10.1006/jcph.1998.6019

WANG Z J. Vortex shedding and frequency selection in flapping flight[J]. Journal of Fluid Mechanics, 2000, 410: 323-341. DOI: 10.1017/s0022112099008071

WANG Z J. Two dimensional mechanism for insect hovering[J]. Physical Review Letters, 2000, 85(10): 2216-2219. DOI: 10.1103/PhysRevLett.85.2216

WANG Z J. The role of drag in insect hovering[J]. The Journal of Experimental Biology, 2004, 207(pt 23): 4147-4155. DOI: 10.1242/jeb.01239

WANG Z J, BIRCH J M, DICKINSON M H. Unsteady forces and flows in low Reynolds number hovering flight: two-dimensional computations vs robotic wing experiments[J]. The Journal of Experimental Biology, 2004, 207(pt 3): 449-460. DOI: 10.1242/jeb.00739

SUN M. Aerodynamics of insect flight[J]. Advances in Mechanics, 2015, 45(1): 1-28. (in Chinese) DOI: 10.6052/1000-0992-14-065

LIANG B, SUN M. Dynamic flight stability of a hovering model dragonfly[J]. Journal of Theoretical Biology, 2014, 348: 100-112. DOI: 10.1016/j.jtbi.2014.01.026

SUN M, LAN S L. A computational study of the aerodynamic forces and power requirements of dragonfly (Aeschna juncea) hovering[J]. The Journal of Experimental Biology, 2004, 207(pt 11): 1887-1901. DOI: 10.1242/jeb.00969

SUN M, TANG J. Unsteady aerodynamic force generation by a model fruit fly wing in flapping motion[J]. The Journal of Experimental Biology, 2002, 205(pt 1): 55-70.

YOUNG J, LAI J C S, GERMAIN C. Simulation and parameter variation of flapping-wing motion based on dragonfly hovering[J]. AIAA Journal, 2008, 46(4): 918-924. DOI: 10.2514/1.31610

HE Y L, WANG Y, LI Q. Lattice Boltzmann method: theory and applications[M]. Beijing: Science Press, 2009. (in Chinese)

MINAMI K, SUZUKI K, INAMURO T. Free flight simulations of a dragonfly-like flapping wing-body model using the immersed boundary-lattice Boltzmann method[J]. Fluid Dynamics Research, 2015, 47(1): 015505. DOI: 10.1088/0169-5983/47/1/015505

OSHER S, SETHIAN J A. Fronts propagating with curvature-dependent speed: Algorithms based on Hamilton-Jacobi formulations[J]. Journal of Computational Physics, 1988, 79(1): 12-49. DOI: 10.1016/0021-9991(88)90002-2

LI H X, DENG S, ZHAO J F, et al. Numerical simulation of interface movement in gas-liquid two-phase flows with level set method[J]. Nuclear Power Engineering, 2005, 26(3): 242-248, 267. (in Chinese)

CHEN F H, WANG C, HAO L, et al. Tracking moving interfaces by level set method[J]. Mechanics in Engineering, 2006, 28(4): 23-27. (in Chinese)

XIAN W, TAKAYUKI A. Multi-GPU performance of incompressible flow computation by lattice Boltzmann method on GPU cluster[J]. Parallel Computing, 2011, 37(9): 521-535. DOI: 10.1016/j.parco.2011.02.007

GUO Z L, ZHENG C G, SHI B C. An extrapolation method for boundary conditions in lattice Boltzmann method[J]. Physics of Fluids, 2002, 14(6): 2007-2010. DOI: 10.1063/1.1471914

CAIAZZO A. Analysis of lattice Boltzmann nodes initialisation in moving boundary problems[J]. Progress in Computational Fluid Dynamics, an International Journal, 2008, 8(1/2/3/4): 3. DOI: 10.1504/pcfd.2008.018074

LI H, LU X, FANG H, et al. Force evaluations in lattice Boltzmann simulations with moving boundaries in two dimensions[J]. Physical Review E, Statistical, Nonlinear, and Soft Matter Physics, 2004, 70(2 pt 2): 026701. DOI: 10.1103/physreve.70.026701

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