Effect of vortex-induced vibration of a small cylinder on airfoil aerodynamics

Dongyang CHEN; Rui XU; Xiang ZHANG; Qifa ZHANG; Xiaoting RUI

doi:10.11990/jheu.202207037

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Effect of vortex-induced vibration of a small cylinder on airfoil aerodynamics

更新时间：2025-09-01

- Effect of vortex-induced vibration of a small cylinder on airfoil aerodynamics
- Journal of Harbin Engineering University Vol. 45, Issue 4, Pages: 739-747(2024)
- 作者机构：
  
  1.西北工业大学海洋研究院, 江苏苏州 215000
  2.浙江金马逊智能制造股份有限公司, 浙江丽水 321403
  3.西北工业大学深圳研究院, 广东深圳 518063
  4.扬州大学电气与能源动力工程学院, 江苏扬州 225100
  5.海油发展珠海管道工程有限公司, 广东珠海 519050
  6.南京理工大学发射动力学研究所, 江苏南京 210094
- 作者简介：
- 基金信息：
- DOI：10.11990/jheu.202207037
  CLC： O353.1
- Received：16 July 2022，
  
  Online First：19 February 2024，
  
  Published：05 April 2024
- 稿件说明：
移动端阅览
Dongyang CHEN, Rui XU, Xiang ZHANG, et al. Effect of vortex-induced vibration of a small cylinder on airfoil aerodynamics[J]. Journal of Harbin Engineering University, 2024, 45(4): 739-747.
DOI：

Dongyang CHEN, Rui XU, Xiang ZHANG, et al. Effect of vortex-induced vibration of a small cylinder on airfoil aerodynamics[J]. Journal of Harbin Engineering University, 2024, 45(4): 739-747. DOI： 10.11990/jheu.202207037.

摘要

在大攻角来流时

翼型吸力面气流常产生流动分离现象

使翼型气动性能恶化。针对大攻角情况下的流动分离现象

本文在翼型前缘加入控制柱

通过数值仿真探究发生涡激振动的小圆柱对于翼型气动力的影响。基于计算流体力学、结构动力学和嵌套网格技术

本文建立了二维流固耦合模型。以NACA0012翼型为例

对翼型前缘设置涡激振动圆柱的流场情况进行模拟

并且对比了静止圆柱与振动圆柱情况下的流场变化。通过流线图和涡量云图分析了小圆柱流动控制的机理。仿真结果表明: 设置静止小圆柱可以提高大攻角下的翼型升阻比

使小圆柱产生涡激振动之后

能够进一步有效地提高大攻角下的翼型升阻比50 %以上。涡激振动小圆柱的引入在大攻角条件下对提升翼型升阻比具有显著效果

为改善翼型气动性能提供了一种有效的流动控制手段。

Abstract

Flow separation often occurs on the suction surface of an airfoil at a high angle of attack

deteriorating the aerodynamic performance of the airfoil. A control column is added at the leading edge of the airfoil to explore the influence of a small cylinder with vortex-induced vibration on the aerodynamic force of the airfoil through numerical simulation. Based on computational fluid dynamics

structural dynamics

and overset mesh technology

this study establishes a 2D-fluid-structure interaction model. Using the NACA0012 airfoil as an example

the flow field of the vortex-induced vibrating cylinder at the leading edge of the airfoil is simulated. The changes in the flow field between stationary and vibrating cylinders are then compared. The flow control mechanism of the small cylinder is analyzed using streamline and vorticity contours. The simulation results show that setting a stationary small cylinder can improve the lift-drag ratio of the airfoil at a high angle of attack. After the small cylinder produces vortex-induced vibration

it can further effectively improve the lift-drag ratio of the airfoil at a high angle of attack by more than 50 %. The introduction of the vortex-induced vibration cylinder considerably enhances the lift-drag ratio of the airfoil at a high angle of attack. This effect implies that the established model is effective for controlling airflow and improving the aerodynamic performance of airfoils.

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