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涡激振动小圆柱对翼型气动力影响的数值研究

陈东阳 徐瑞 张祥 张启发 芮筱亭

哈尔滨工程大学学报2024,Vol.45Issue(4):739-747,9.
哈尔滨工程大学学报2024,Vol.45Issue(4):739-747,9.DOI:10.11990/jheu.202207037

涡激振动小圆柱对翼型气动力影响的数值研究

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

陈东阳 1徐瑞 2张祥 3张启发 3芮筱亭4

作者信息

  • 1. 西北工业大学 海洋研究院,江苏 苏州 215000||浙江金马逊智能制造股份有限公司,浙江 丽水 321403||西北工业大学深圳研究院,广东 深圳 518063
  • 2. 扬州大学 电气与能源动力工程学院,江苏 扬州 225100
  • 3. 海油发展珠海管道工程有限公司,广东 珠海 519050
  • 4. 南京理工大学 发射动力学研究所,江苏 南京 210094
  • 折叠

摘要

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 numer-ical 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-in-duced 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.

关键词

数值模拟/流动分离/涡激振动/计算流体力学/翼型/结构动力学/柱体/嵌套网格

Key words

numerical simulation/flow separation/vortex-induced vibration/computational fluid dynamics/airfoil/structural dynamics/cylinder/overset mesh

分类

数理科学

引用本文复制引用

陈东阳,徐瑞,张祥,张启发,芮筱亭..涡激振动小圆柱对翼型气动力影响的数值研究[J].哈尔滨工程大学学报,2024,45(4):739-747,9.

基金项目

中国博士后科学基金项目(2023M743108) (2023M743108)

广东省基础与应用基础研究基金项目(2024A1515011046) (2024A1515011046)

浙江省领军型创新创业团队项目(2022R01012) (2022R01012)

姑苏青年创新领军人才项目(ZXL2023168). (ZXL2023168)

哈尔滨工程大学学报

OA北大核心CSTPCD

1006-7043

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