用于飞机机翼涡固干扰噪声数值模拟的RANS/NLAS方法

刘菲菲 1; 2; 陈刚 2; 李跃明 2

doi:10.7652/xjtuxb201509023

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用于飞机机翼涡固干扰噪声数值模拟的RANS/NLAS方法

更新时间：2025-07-09

- 用于飞机机翼涡固干扰噪声数值模拟的RANS/NLAS方法
- An RANS/NLAS-Based Numerical Simulation for the Prediction of Aerodynamic Noise Due to Vortex-Structure Interaction of Airfoil
- 西安交通大学学报 2015年49卷第9期页码：141-146
- 作者机构：
  
  1. 中国空气动力研究与发展中心,四川,绵阳,621000
  2. 西安交通大学航天航空学院,西安,710049
- 作者简介：
- 基金信息：
  
  : 2014-01-21。作者简介: 刘菲菲(1987—),女,硕士生;陈刚(通信作者),男,教授,博士生导师。基金项目: 国家“973计划”资助项目(2013CB03570202);国家自然科学基金资助项目(11272005,1141101165)
- DOI：10.7652/xjtuxb201509023
  中图分类号： V211.3
- 网络首发：2015-09-10，
  
  纸质出版：2015
- 稿件说明：
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刘菲菲 1, 2, 陈刚 2, 等. 用于飞机机翼涡固干扰噪声数值模拟的RANS/NLAS方法[J]. 西安交通大学学报, 2015,49(9):141-146.

An RANS/NLAS-Based Numerical Simulation for the Prediction of Aerodynamic Noise Due to Vortex-Structure Interaction of Airfoil[J]. 2015, 49(9): 141-146.
刘菲菲 1, 2, 陈刚 2, 等. 用于飞机机翼涡固干扰噪声数值模拟的RANS/NLAS方法[J]. 西安交通大学学报, 2015,49(9):141-146. DOI： 10.7652/xjtuxb201509023.

An RANS/NLAS-Based Numerical Simulation for the Prediction of Aerodynamic Noise Due to Vortex-Structure Interaction of Airfoil[J]. 2015, 49(9): 141-146. DOI： 10.7652/xjtuxb201509023.

摘要

针对传统的气动噪声混合模拟方法对网格要求过高的问题

尝试将非线性声学方程应用于涡固干扰噪声的计算中

以串列柱-翼模型作为飞机关键噪声部件的典型模型

利用数值模拟方法来研究涡固干扰噪声机理。通过雷诺平均N-S方程(RANS)求解流场信息

再通过非线性声学方程(NLAS)求解声场

获得串列柱-翼模型典型位置处的流场特性和噪声预测结果

揭示了涡固干扰噪声机制。RANS/NLAS方法对计算网格要求低、节约计算资源、缩短计算时间且计算精度高

可较准确地模拟非线性噪声。模拟计算表明:非定常来流下

涡固干扰是造成机翼噪声的最主要原因

主要发声部位由机翼后缘移至前缘

串列柱-翼模型噪声的单音峰值出现在频率1 354 Hz处

最大声压级为91 dB。对近场流动特性和远场噪声预测的结果

与文献中实验结果均取得很好的一致性。

Abstract

The aerodynamic noise caused by vortex-structure interaction is becoming one of the main research hotspots in aeronautics. The paper takes rod-airfoil model as the research object to conduct acoustic analogy through NLAS and CFD analysis through RANS

to investigate the mechanism of this kind of noise. Compared with the traditional analogy methods

RANS/NLAS method can simulate the nonlinear noise more accurately with less gird requirements

higher accuracy and is easy to be implemented. The results show that the vortex-structure interaction is the main cause of airfoil noise and leading edge is the major noise source position. Meanwhile

the RANS/NLAS method can successfully predict vortex-structure interaction in near-field and the noise spectra in far-field

which is in accord with the earlier experimental research.

关键词

Keywords

references

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