Application of 5.5 m × 4 m aeroacoustic wind tunnel in Sino-Russia joint research collaboration on landing gear noise and its control

ZHAO Kun; WANG Xunnian; SONG Yubao; FAN Zhenglei; KOPIEV Victor

doi:10.7638/kqdlxxb-2022.0152

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Application of 5.5 m × 4 m aeroacoustic wind tunnel in Sino-Russia joint research collaboration on landing gear noise and its control

更新时间：2026-05-28

- Application of 5.5 m × 4 m aeroacoustic wind tunnel in Sino-Russia joint research collaboration on landing gear noise and its control
- Vol. 41, Issue 1, Pages: 66-76(2023)
- 作者机构：
  
  1. 中国空气动力研究与发展中心低速空气动力研究所，气动噪声控制重点实验室,绵阳,621000
  2. 俄罗斯中央空气流体动力研究院气动噪声部,莫斯科,俄罗斯,105005
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2022.0152
  CLC： V216.3
- Published：2023
- 稿件说明：
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赵鲲, 王勋年, 宋玉宝, 等. 5.5 m × 4 m声学风洞在中俄民机起落架噪声特性及控制技术联合研究中的应用[J]. 空气动力学学报, 2023, 41(1): 66−76.

ZHAO Kun, WANG Xunnian, SONG Yubao, et al. Application of 5.5 m × 4 m aeroacoustic wind tunnel in Sino-Russia joint research collaboration on landing gear noise and its control[J]. 2023, 41(1): 66-76.
赵鲲, 王勋年, 宋玉宝, 等. 5.5 m × 4 m声学风洞在中俄民机起落架噪声特性及控制技术联合研究中的应用[J]. 空气动力学学报, 2023, 41(1): 66−76. DOI： 10.7638/kqdlxxb-2022.0152

ZHAO Kun, WANG Xunnian, SONG Yubao, et al. Application of 5.5 m × 4 m aeroacoustic wind tunnel in Sino-Russia joint research collaboration on landing gear noise and its control[J]. 2023, 41(1): 66-76. DOI： 10.7638/kqdlxxb-2022.0152.

摘要

以中国-俄罗斯民用飞机起落架噪声特性及控制技术联合研究中所使用的5.5 m × 4 m声学风洞（FL-17 风洞）为例，介绍了大型声学风洞在科研工作中的应用情况。首先介绍了FL-17风洞的研制历程与各项性能指标；然后基于中俄联合研究中的大尺度起落架气动噪声风洞试验，概述了起落架噪声相关领域的研究现状，以及利用FL-17风洞开展的起落架噪声机理与控制技术方面的研究内容与成果，如试验、数值模拟和噪声预测数据库，以及基于非常规截面方法和空气幕方法的起落架降噪技术等；最后，对于大型声学风洞的科研使用给出了一些经验和建议。

Abstract

Regarding applications of the large-scale aeroacoustic wind tunnel in scientific research

this paper introduces the usage of FL-17

a 5.5 m × 4 m aeroacoustic wind tunnel

in a Sino-Russia joint collaboration research project on civil aircraft landing gear noise and its control. First of all

the construction history and specifications of FL-17 wind tunnel are introduced. Then

based on the large-scale wind tunnel test of landing gear aerodynamic noise in Sino-Russia joint research

the state-of-the-art of the landing gear noise investigation was introduced

as well as the research contents and achievements of the landing gear noise and its control carried out in FL-17 wind tunnel. The discussions involve large-scale experimental studies

database of full-scale landing gear experiment

numerical simulations

prediction models

noise control using truncated cylinders and air curtains

etc. As last

some experiences and suggestions on the usage of large-scale aeroacoustic wind tunnel were provided.

关键词

Keywords

references

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