Interactive Effects of Wind Tunnel Sidewalls on Flow Structures around 2D Airfoil Model

BAI Jingyan, ZHANG Lei, YANG Ke, ZHAO Daiqing, XU Jianzhong

热科学学报 ›› 2023, Vol. 32 ›› Issue (2) : 708-717.

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PDF(12397 KB)
热科学学报 ›› 2023, Vol. 32 ›› Issue (2) : 708-717. DOI: 10.1007/s11630-023-1753-7  CSTR: 32141.14.JTS-023-1753-7

Interactive Effects of Wind Tunnel Sidewalls on Flow Structures around 2D Airfoil Model

  • BAI Jingyan1,2,3,4, ZHANG Lei2,4*, YANG Ke2, ZHAO Daiqing1, XU Jianzhong2,4
作者信息 +

Interactive Effects of Wind Tunnel Sidewalls on Flow Structures around 2D Airfoil Model

  • BAI Jingyan1,2,3,4, ZHANG Lei2,4*, YANG Ke2, ZHAO Daiqing1, XU Jianzhong2,4
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摘要

本文采用风洞试验与数值模拟方法分析了风洞侧壁对风力机翼型表面流动特性的影响,风洞试验在低速风洞中开展,雷诺数为2.62×105,通过表面测压法获得风洞侧壁干扰下翼型表面的压力特性,通过油流试验法获得风洞侧壁干扰下翼型表面的流动结构。通过对数值模拟方和试验测量方法的结果进行分析,得出:在小攻角时,在风洞侧壁边界层与翼型表面边界层相互作用下,仅在翼型模型与侧壁连接处形成较小的角区分离涡。随着攻角的增加,角区分离涡增大。当翼型表面流动发生失速分离时,在翼型中间部分,形成了三维失速胞。随着攻角进一步增加,三维失速胞会从翼型中间部分向翼型段两侧发展,进而抑制角区分离涡的产生和发展,同时其发展也受到了风洞侧壁边界层的限制。通过分析也得出风洞侧壁边界层的存在会引起压力系数降低,在大攻角下,通过消除风洞侧壁分离涡可以使得翼型表面保持二维流动特性。

Abstract

This paper presents the effect of wind tunnel sidewalls on the wind turbine airfoils with experimental and numerical methods. The test is carried out in a low-speed wind tunnel at Re=2.62×105. Pressures acting on the airfoil surface are measured by a multiport pressure device. And, the oil flow visualization technique is used to investigate the flow field characteristics of the airfoil surface. Then, a numerical simulation was conducted with the measurement results. As a result, it is clarified the flow structures on the airfoil surface depend strongly on the angles of attack and the sidewalls. At small angles of attack, the three-dimensional separation caused by the interaction between the sidewall boundary layer and the airfoil boundary layer is very small, and only appears near the junction of the airfoil model and the sidewall. This corner separation becomes large with the increase of the angle of attack. At the middle part of the testing model, the boundary layer flow evolves into three-dimensional separation, i.e., stall cell, when the separation develops to an appreciate extent. The stall phenomenon will further spread from the center line to sidewalls with the increase of the angle of attack; and then, its development will be limited by the sidewall boundary layer separation. Comparably, the simulation shows that the sidewall make the pressure coefficient Cp decrease, and proper boundary condition can maintain two-dimensional flow at large angles of attack by eliminating the influence of corner vortices.

关键词

airfoil / experiment / sidewall / corner vortex / stall cell / airfoil-wall junction

Key words

airfoil / experiment / sidewall / corner vortex / stall cell / airfoil-wall junction

引用本文

导出引用
BAI Jingyan, ZHANG Lei, YANG Ke, ZHAO Daiqing, XU Jianzhong. Interactive Effects of Wind Tunnel Sidewalls on Flow Structures around 2D Airfoil Model[J]. 热科学学报, 2023, 32(2): 708-717 https://doi.org/10.1007/s11630-023-1753-7
BAI Jingyan, ZHANG Lei, YANG Ke, ZHAO Daiqing, XU Jianzhong. Interactive Effects of Wind Tunnel Sidewalls on Flow Structures around 2D Airfoil Model[J]. Journal of Thermal Science, 2023, 32(2): 708-717 https://doi.org/10.1007/s11630-023-1753-7

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基金

This research was funded by the National Natural Science Foundation of China (No. 51776204). The authors acknowledge the participants of the program and their contributions.

版权

Science Press, Institute of Engineering Thermophysics, CAS and Springer-Verlag GmbH Germany, part of Springer Nature 2023
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