拐角扩张比与导流片安装角对BHAW风洞流场品质影响的数值研究

刘沛清; 陈阅; 张瑾; 屈秋林

doi:10.7638/kqdlxxb-2023.0006

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拐角扩张比与导流片安装角对BHAW风洞流场品质影响的数值研究

研究论文 | 更新时间：2026-05-28

- 拐角扩张比与导流片安装角对BHAW风洞流场品质影响的数值研究
- Numerical study of the effects of corner expansion ratio and installation angle of guide vanes on flow fields in BHAW wind tunnel
- 空气动力学学报 2023年41卷第9期页码：82-95
- 作者机构：
  
  1. 北京航空航天大学航空气动声学工业和信息化部重点实验室,北京,100191
  2. 北京航空航天大学航空科学与工程学院,北京,100191
  3. 北京航空航天大学中法工程师学院/国际通用工程学院,北京,100191
- 作者简介：
  
  刘沛清，男，教授，博士生导师，研究方向：气动噪声，旋涡分离流与流动控制，低雷诺数流动机理，飞行器布局与大迎角空气动力学，螺旋桨设计与优化，大型飞机起飞着陆与水上迫降性能，等. E-mail：lpq@buaa.edu.cn
  张瑾*，女，副教授，硕士生导师，研究方向：气动噪声数值模拟，计算流体力学，辐射换热数值模拟. E-mail：jin_zhang@buaa.edu.cn
- 基金信息：
  
  国家自然科学基金（122720）;气动噪声控制重点实验室开放课题( 2002ANCL20200102 )
- DOI：10.7638/kqdlxxb-2023.0006
  中图分类号： V211.74
- 纸质出版：2023
- 稿件说明：
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刘沛清, 陈阅, 张瑾, 等. 拐角扩张比与导流片安装角对BHAW风洞流场品质影响的数值研究[J]. 空气动力学学报, 2023, 41(9): 82−95.

LIU Peiqing, CHEN Yue, ZHANG Jin, et al. Numerical study of the effects of corner expansion ratio and installation angle of guide vanes on flow fields in BHAW wind tunnel[J]. 2023, 41(9): 82-95.
刘沛清, 陈阅, 张瑾, 等. 拐角扩张比与导流片安装角对BHAW风洞流场品质影响的数值研究[J]. 空气动力学学报, 2023, 41(9): 82−95. DOI： 10.7638/kqdlxxb-2023.0006

LIU Peiqing, CHEN Yue, ZHANG Jin, et al. Numerical study of the effects of corner expansion ratio and installation angle of guide vanes on flow fields in BHAW wind tunnel[J]. 2023, 41(9): 82-95. DOI： 10.7638/kqdlxxb-2023.0006.

摘要

以北京航空航天大学4 m × 3 m低湍流强度、低背景噪声的大型封闭回路气动声学风洞（BHAW）设计需求为工程应用背景，采用

SST湍流模型进行了数值模拟，分析了在多个扩张比下的拐角导流片安装角对流场的影响。研究结果验证了在不同拐角扩张比下的总压损失系数均随导流片安装角增大而先减小后增大，且存在极小值点，极值点对应的导流片安装角与拐角扩张比呈现正相关。在不同的扩张比下，局部损失系数均随导流片安装角增大呈现先减小后增大的变化规律；相同导流片安装角下，拐角中部导流片的摩擦损失系数最大，导流片安装角的变化对中部导流片（即6～8号导流片）的流速影响较小；随着拐角扩张比增大，拐角出口管道内气流不均匀性增大，最佳导流效果的导流片对应的安装角增大。在综合考虑降低总压损失系数和减小管道出口气流偏角两个设计原则后，BHAW风洞为扩张比为1.17的第一拐角选择44°的设计安装角，为扩张比为1的第二、三、四拐角选择44°、43°、42.5°的设计安装角。通过数值计算验证了风洞试验段的核心区动压系数小于0.2%、速度水平偏角小于0.1°，满足BHAW气动设计要求。

Abstract

This article aims to provide technical support for designing the large closed-loop aeroacoustics wind tunnel with low turbulence intensity and low background noise at Beihang University (BHAW). The effects of the corner guide vanes angle on the flow fields are analyzed for several different expansion ratios by numerical simulations with the

SST turbulence model

and the optimal installation angle of guide vanes for the BHAW wind tunnel is determ

ined. Numerical results reveal that the pressure loss coefficient decreases first and then increases with the augmentation of the installation angle of guide vanes at each corner expansion ratio. The results further indicate the existence of a minimum pressure loss coefficient

and the installation angle of the guide vanes corresponding to the minimum value has a positive correlation with the corner expansion ratio. With various expansion ratios

the local pressure loss initially decreases and then increases with the guide vanes installation angle. The results demonstrate that the maximum friction loss coefficient occurs at the middle of the guide plate for a given installation angle; the installation angle mildly affects the flow around the central guide vanes (guide vanes 6

and 8). With the increase of the corner expansion ratio

the flow velocity uniformity at the corner outlet deteriorates

and the installation angle of the guide vanes with the best flow guiding effect increases. By minimizing the total pressure loss coefficient and velocity deflection angle at the pipeline outlet

BHAW adopted an installation angle of 44° for the first corner with an expansion ratio of 1.17

an installation angle of 44° for the second corner with an expansion ratio of 1

an installation angle of 43° for the third corner with an expansion ratio of 1

and an installation angle of 42.5° for the fourth corner with an expansion ratio of 1. Such a strategy results in the dynamic pressure coefficient in the core area of the wind tunnel test section being less than 0.2% and the horizontal velocity deflection angle being less than 0.1°

justifying the aerodynamic design of BHAW.

关键词

Keywords

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