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翼型湍流尾缘噪声半经验预测公式改进

柏宝红 李晓东

柏宝红, 李晓东. 翼型湍流尾缘噪声半经验预测公式改进[J]. 北京航空航天大学学报, 2017, 43(1): 86-92. doi: 10.13700/j.bh.1001-5965.2016.0076
引用本文: 柏宝红, 李晓东. 翼型湍流尾缘噪声半经验预测公式改进[J]. 北京航空航天大学学报, 2017, 43(1): 86-92. doi: 10.13700/j.bh.1001-5965.2016.0076
BAI Baohong, LI Xiaodong. Improvement of airfoil turbulent trailing-edge noise semi-empirical prediction formulation[J]. Journal of Beijing University of Aeronautics and Astronautics, 2017, 43(1): 86-92. doi: 10.13700/j.bh.1001-5965.2016.0076(in Chinese)
Citation: BAI Baohong, LI Xiaodong. Improvement of airfoil turbulent trailing-edge noise semi-empirical prediction formulation[J]. Journal of Beijing University of Aeronautics and Astronautics, 2017, 43(1): 86-92. doi: 10.13700/j.bh.1001-5965.2016.0076(in Chinese)

翼型湍流尾缘噪声半经验预测公式改进

doi: 10.13700/j.bh.1001-5965.2016.0076
基金项目: 

国家“973”计划 2012CB720202

国家自然科学基金 National Natural Science Foundation of China

详细信息
    作者简介:

    柏宝红, 男, 博士研究生。主要研究方向:气动声学

    通讯作者:

    李晓东, 男, 博士, 教授。主要研究方向:气动声学、计算气动声学。E-mail:lixd@buaa.edu.cn

  • 中图分类号: V211

Improvement of airfoil turbulent trailing-edge noise semi-empirical prediction formulation

Funds: 

National Basic Research Program of China 2012CB720202

英文基金项目 National Natural Science Foundation of China

More Information
  • 摘要:

    改进了传统的翼型湍流边界层尾缘噪声BPM半经验预测公式。传统的BPM半经验湍流边界层尾缘噪声预测公式对高攻角和厚翼型在高频范围的预测结果大于实验结果,通过分析比较传统BPM半经验预测公式和Howe翼型尾缘噪声理论模型发现:这主要是由于传统BPM半经验预测公式对压力面声源噪声辐射高估引起的。因此将压力面声源噪声辐射与吸力面声源噪声辐射的幅值比由原来的边界层位移厚度一次方比值改进为二次方比值,进而得到了改进后的BPM半经验预测公式;使用改进后的BPM半经验预测公式对NACA0012翼型在不同来流不同攻角下的噪声辐射进行了预测比较,发现对于NACA0012翼型,改进后的BPM半经验预测公式具有较高精度;另外也预测了较厚的风力机翼型DU-96-W-180,预测结果明显改善。

     

  • 图 1  边界层位移厚度随攻角的变化

    Figure 1.  Variation of boundary displacement thickness withangle of attack

    图 2  边界层动量厚度随攻角的变化

    Figure 2.  Variation of boundary momentum thickness withangle of attack

    图 3  攻角为0时边界层厚度随雷诺数的变化

    Figure 3.  Variation of boundary thickness with Reynolds numberwhen angle of attack equals to zero

    图 4  工况1~工况5的噪声预测对比

    Figure 4.  Comparison of noise prediction for Case 1-Case 5

    表  1  计算工况

    Table  1.   Computation cases

    工况翼型U/ (m·s-1)Re/106α/(°)
    1NACA001256.01.50
    2NACA001254.81.54
    3NACA001253.01.56
    4NACA001237.71.00
    5DU-96-W-18060.01.14
    下载: 导出CSV
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出版历程
  • 收稿日期:  2016-01-21
  • 录用日期:  2016-03-11
  • 刊出日期:  2017-01-20

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