大型气动声学风洞折线型集气口段流场特性数值研究与试验验证

刘沛清; 陈阅; 马利川; 郭昊; 梁雯智; 侯强中; 张瑾; 屈秋林; 胡天翔

doi:10.7638/kqdlxxb-2025.0048

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大型气动声学风洞折线型集气口段流场特性数值研究与试验验证

研究论文 | 更新时间：2026-05-28

- 大型气动声学风洞折线型集气口段流场特性数值研究与试验验证
- Numerical and experimental study of flow field characteristics of the zigzag-shaped collector in a large-scale aeroacoustic wind tunnel
- 空气动力学学报 2025年43卷第11期页码：1-15
- 作者机构：
  
  1. 北京航空航天大学航空气动声学工信部重点实验室,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*（1960—），男，山西忻州人，研究方向：旋涡分离与控制、高速层流控制技术. E-mail：lpq@buaa.edu.cn
- 基金信息：
  
  国家大型设施资助计划
- DOI：10.7638/kqdlxxb-2025.0048
  中图分类号： V211.74
- 纸质出版：2025
- 稿件说明：
移动端阅览
刘沛清, 陈阅, 马利川, 等. 大型气动声学风洞折线型集气口段流场特性数值研究与试验验证[J]. 空气动力学学报, 2025, 43(11): 1−15.

LIU Peiqing, CHEN Yue, MA Lichuan, et al. Numerical and experimental study of flow field characteristics of the zigzag-shaped collector in a large-scale aeroacoustic wind tunnel[J]. 2025, 43(11): 1-15.
刘沛清, 陈阅, 马利川, 等. 大型气动声学风洞折线型集气口段流场特性数值研究与试验验证[J]. 空气动力学学报, 2025, 43(11): 1−15. DOI： 10.7638/kqdlxxb-2025.0048

LIU Peiqing, CHEN Yue, MA Lichuan, et al. Numerical and experimental study of flow field characteristics of the zigzag-shaped collector in a large-scale aeroacoustic wind tunnel[J]. 2025, 43(11): 1-15. DOI： 10.7638/kqdlxxb-2025.0048.

摘要

北京航空航天大学4 m×3 m大型全声衬低湍流度、低噪声气动声学风洞（Beihang University Acoustic Wind Tunnel

BHAW）主要用于大型飞机机体部件气动噪声机理与降噪技术研究。集气口段的几何外形和结构尺寸，对引导气流、降低流动冲击及抑制低频脉动和噪声具有重要作用。本文在系统分析声学风洞试验段射流对不同集气口外形冲击与绕流特性的基础上，首次提出了一种折线集气口型，并通过三维数值模拟对其外形尺寸进行了优化。最终确定BHAW风洞集气口结构参数为：集气口末端截面积与试验段截面积之比为 1.352，入口段水平直段长度与试验段长度之比约为10%，圆形唇口半径与试验段出口高度之比为 0.085，单边收缩角为 8°。数值模拟结果表明，当集气口段收缩角超过8°时，气流出现明显分离，且随着角度增大，分离区逐步扩展，冲击面积比线性增大。大涡模拟显示，折线型集气口的壁面压强脉动较小，主要涡结构为射流边界层的脱落涡，频率为13.3 Hz，相应的斯特劳哈尔数

为0.57。风洞测量结果表明：在闭口试验段风速35～100 m/s范围内，动压稳定性系数为

0.00197

～0.001，达到国军标先进指标

$ \leqslant $0.002要求；在开口试验段风速35～80 m/s范围内，动压稳定性系数为

0.0048

～

0.0036

，达到国军标合格指标

$\leqslant $0.005要求，且为闭口试验段的2.4～3.6倍；在设计风速下，开口试验段模型区动压场系数分布$ \left| {{\mu _{\text{i}}}} \right| \leqslant$0.5%，满足国军标合格指标要求，在闭口试验段模型区内$ \left| {{\mu _{\text{i}}}} \right| \leqslant $0.2%，满足国军标先进指标要求；在开口试验段设计风速80 m/s下，风洞远场噪声级为74.0～74.4 dB(A)。与RTR

I风洞相比，BHAW风洞在低频区噪声降低约7 dB，高频区噪声水平两者相当，整体声压级比RTRI风洞低1～0.6 dB。综上所述，折线型集气口设计方案合理可行，能够有效稳定试验段气流场，降低噪声和湍流度，具有较强的工程应用潜力。

Abstract

The Beihang University Acoustic Wind Tunnel (BHAW)

with dimensions of 4 m × 3 m

is a large-scale low-turbulence

low-noise aeroacoustic wind tunnel primarily used for studying the aerodynamic noise mechanisms and noise reduction technologies of large aircraft components. During wind tunnel operation

the geometry and structural dimensions of the collector section play a crucial role in smoothly guiding the airflow

reducing airflow impact on the walls

and mitigating low-frequency pulsations and noise in the collector section. Based on a systematic analysis of the impact of test section jet on different collector configurations and their flow characteristics

this study introduces a novel zigzag-shaped collector design and optimizes its dimensions through three-dimensional numerical simulations. The final selected structural parameters for the BHAW wind tunnel's collector are as follows: the ratio of the collector's exit area to the test section's cross-sectional area is 1.352; the ratio of the length of the horizontal straight segment at the inlet to the length of the test section is approximately 10%; the ratio of the radius of the circular lip to the height of the test section exit is 0.085; and the single-side contraction angle is 8°. Numerical simulation results indicate that when the contraction angle of the collector section exceeds 8°

significant flow separation occurs

and the separation region expands progressively with increasing angle. The impingement area ratio increases approximately linearly with the angle. In contrast

the zigzag-shaped collector effectively prevents flow separation

ensuring that the jet impingement point consistently remains at the lip

thereby maintaining stable flow characteristics. Large eddy simulation (LES) results further demonstrate that the wall pressure fluctuations in the zi

gzag-shaped collector are relatively small. The dominant vortex structures are primarily shedding vortices from the jet boundary layer

with a characteristic frequency of 13.3 Hz and a corresponding Strouhal number (

) of 0.57. Wind tunnel measurements indicate that within the velocity range of 35–100 m/s in the closed test section

the dynamic pressure stability coefficient ranges from

0.00197

to 0.001

satisfying the advanced standard

$\leqslant $0.002. In the open test section

under 35–80 m/s

the coefficient ranges from

0.0048

0.0036

meeting the basic standard

$ \leqslant $0.005. The pressure stability coefficient in the open section is approximately 2.4 to 3.6 times that of the closed section.The dynamic pressure coefficient distribution in the model region of the open test section is within ±0.5% at the design velocity

meeting the basic qualification criteria of the National Military Standard of China (GJB). For the closed test section

the distribution is within ±0.2%

meeting the advanced criteria of the same standard. At the design speed of 80 m/s

the far-field noise level of the open test section is measured to be between 74.0 and 74.4 dB(A). Compared with the RTRI wind tunnel

the BHAW tunnel achieves approximately 7 dB noise reduction in the low-frequency range

exhibits comparable noise levels in the high-frequency range

and has an overall sound pressure level that is 0.6–1.0 dB lower than that of the RTRI. In summary

the zigzag-shaped collector design is rational and effective

enabling stable flow in the test section and reducing both turbulence and noise

thereby demonstrating strong potential for practical engineering applications.

关键词

Keywords

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