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基于脉压波数频率谱的翼型尾缘散射噪声预测

余荣科 冯和英 赵鲲 肖春华 彭睿哲 郭鹏

余荣科, 冯和英, 赵鲲, 等. 基于脉压波数频率谱的翼型尾缘散射噪声预测[J]. 航空动力学报, 2024, 39(X):20230450 doi: 10.13224/j.cnki.jasp.20230450
引用本文: 余荣科, 冯和英, 赵鲲, 等. 基于脉压波数频率谱的翼型尾缘散射噪声预测[J]. 航空动力学报, 2024, 39(X):20230450 doi: 10.13224/j.cnki.jasp.20230450
YU Rongke, FENG Heying, ZHAO Kun, et al. Trailing edge scattering noise prediction based on wavenumber-frequency spectrum of pressure fluctuation[J]. Journal of Aerospace Power, 2024, 39(X):20230450 doi: 10.13224/j.cnki.jasp.20230450
Citation: YU Rongke, FENG Heying, ZHAO Kun, et al. Trailing edge scattering noise prediction based on wavenumber-frequency spectrum of pressure fluctuation[J]. Journal of Aerospace Power, 2024, 39(X):20230450 doi: 10.13224/j.cnki.jasp.20230450

基于脉压波数频率谱的翼型尾缘散射噪声预测

doi: 10.13224/j.cnki.jasp.20230450
基金项目: 青年人才托举工程项目(2020-xxxx-QT-xxx); 国家自然科学基金(52375090); 基础加强项目(2022-xxxxx-128); 湖南省自然科学基金项目(2022JJ30249,2020JJ4306)
详细信息
    作者简介:

    余荣科(1998-),男,硕士生,主要从事翼型尾缘噪声快速预测方法研究。E-mail:yk9411@126.com

    通讯作者:

    冯和英(1983-),教授,博士生导师,博士。E-mail:fengheying@hnust.edu.cn

  • 中图分类号: V211.7

Trailing edge scattering noise prediction based on wavenumber-frequency spectrum of pressure fluctuation

  • 摘要:

    基于湍流边界层脉动压力波数-频率谱建模的TNO模型是一种翼型尾缘散射噪声快速预测模型。但TNO(荷兰国家应用科学研究院)模型所采用的波数-频率谱忽略了脉动压力源项中的湍流-湍流项(TT项),导致中高频段噪声预测存在较大偏差。为此,优化模型的流场输入,并引入Chase I模型的TT项,以提高模型的准确性。基于风洞实验获得的NACA0018翼型远场噪声数据,验证了改进后模型的有效性,结果显示:相较于原始模型采用XFOIL方法计算流场作为波数-频率谱的输入,采用RANS方法来计算流场输入更为准确;关于高波数区波数-频率谱幅值的预测,是否引入TT项对预测结果的影响较大;改进后的尾缘散射噪声快速预测方法对高频段噪声的预测精度有明显提升;改进前的TNO模型存在噪声预测偏差随着攻角的增大而增大的问题,改进后的模型对此问题有明显缓解。

     

  • 图 1  翼型结构网格示意图

    Figure 1.  Schematic diagram of airfoil structure grid

    图 2  计算域及边界条件示意图

    Figure 2.  Calculation domain and boundary conditions

    图 3  网格无关性验证

    Figure 3.  Grid independence verification

    图 4  Re=1×106α=0°时表面压力系数对比

    Figure 4.  Re=1×106, α=0°, comparison of surface pressure coefficient

    图 5  远场测量装置布置示意图

    Figure 5.  Arrangement of far-field measuring devices

    图 6  0.55 m × 0.4 m声学风洞开口实验段及实验装置

    Figure 6.  0.55 m × 0.4 m acoustic wind tunnel opening test section and experimental equipment

    图 7  NACA0018实验模型

    Figure 7.  NACA0018 experimental model

    图 8  远场声压级重复性测量结果

    Figure 8.  Repeatability measurement results of far-field sound pressure level

    图 9  α=0°时,不同流速下XFOIL方法和RANS方法噪声预测与实验结果对比

    Figure 9.  Comparison of XFOIL and RANS noise prediction with experimental results at different inflow velocities at α=0º

    图 10  同一来流速度,α=0°~3°时,XFOIL和RANS噪声预测与实验结果对比

    Figure 10.  Comparison of XFOIL and RANS noise prediction with experimental results at the same incoming flow velocity, α=0°~3°

    图 11  U0=50 m/s、α=0°、f=2 000 Hz时,波数-频率谱三维图

    Figure 11.  Three-dimensional diagram of wavenumber-frequency spectrum at U0=50 m/s、α=0°、f=2 000 Hz

    图 12  U0=50 m/s、α=0°、f=2000 Hz时,k1方向波数-频率谱

    Figure 12.  Wavenumber-frequency spectrum in k1 direction at U0=50 m/s、α=0°、f=2000 Hz

    图 13  α=0°时,不同来流速度,原始TNO模型与改进后模型结果对比

    Figure 13.  Comparison of the results of the original TNO model and the improved model at different inflow velocities at α=0°

    图 14  U0=50 m/s,α=0°~3°时,原始TNO模型与改进后模型预测结果对比

    Figure 14.  Comparison of prediction results between the original TNO model and the improved model at U0=50 m/s,α=0°~3°

    图 15  α=0°,U0=44.3,65 m/s 时,总声压级指向分布

    Figure 15.  Overall sound pressure directivity distribution at α=0°,U0=44.3,65 m/s

    图 16  α=3°,U0=44.3m/s、65m/s 时,总声压级指向分布

    Figure 16.  Overall sound pressure directivity distribution at α=3°,U0=44.3,65 m/s

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  • 收稿日期:  2023-07-12
  • 网络出版日期:  2024-06-07

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