迎角对扑翼运动气动性能影响的高性能数值研究

祝衔琦; 孙祥程; 王娴

doi:10.7638/kqdlxxb-2021.0038

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迎角对扑翼运动气动性能影响的高性能数值研究

研究论文 | 更新时间：2026-05-28

- 迎角对扑翼运动气动性能影响的高性能数值研究
- Numerical study of high performance on the influence of angle of attack on aerodynamic performance of wing flapping
- 空气动力学学报 2022年40卷第5期页码：50-60
- 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：
  
  祝衔琦（1997-），男，浙江余姚人，硕士研究生，研究方向：基于LBM-GPUs的蜻蜓扑翼运动机理研究. E-mail：zxqyuyao@stu.xjtu.edu.cn
  王娴*（1977-），女，博士，教授，研究方向：计算流体力学，数值传热学. E-mail：wangxian@mail.xjtu.edu.cn
- 基金信息：
  
  国家数值风洞工程 (NNW)
- DOI：10.7638/kqdlxxb-2021.0038
  中图分类号： V276
- 纸质出版：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.

关键词

Keywords

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