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An investigation of airfoil tonal noise at different Reynolds numbers and angles of attack

机译：不同雷诺数和迎角下的机翼音调噪声研究

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摘要

This paper presents the results of an experimental study into the aeroacoustics of airfoil instability noise and a linear stability analysis of the Tollmien-Schlichting (T-S) waves which develop on the pressure surface. The far field noise produced by a NACA0012 airfoil was measured in a low-noise and low-turbulence open jet wind tunnel. Noise measurements were made at the three angles of attack: 0°, 1.4° and 4.2°, and covered a range of Reynolds numbers between 1.0 × 10~5 and 6.0 × 10~5. An improved understanding of the causal link between the radiated tonal noise and the hydrodynamic instabilities which develop on the pressure surface of an airfoil for a wide range of Reynolds numbers and angles of attack is reported in this paper. The tonal noise produced by the boundary layer which develop on the suction surface was found to be negligible. It was also observed that the total T-S wave amplification on the pressure surface was generally in good agreement with the measured noise spectra. Based on the experimental and predicted data presented in this paper, it was found that effective tone noise generation requires the incoming T-S waves to be amplified by a separated boundary layer first. As the angle of attack increases, the change in pressure gradient on the pressure surface causes the instability noise to change from a broadband hump of moderate intensity level to become more tonal of higher noise intensity.
机译：本文介绍了对翼型不稳定性噪声的航空声学进行实验研究的结果，以及在压力表面上产生的Tollmien-Schlichting（T-S）波的线性稳定性分析。由NACA0012机翼产生的远场噪声是在低噪声，低湍流的露天喷气风洞中测量的。在三个迎角（0°，1.4°和4.2°）上进行了噪声测量，覆盖了雷诺数在1.0×10〜5和6.0×10〜5之间的范围。本文报道了对广泛的雷诺数和迎角范围的机翼压力表面上辐射的音调噪声与流体动力不稳定性之间因果关系的更好理解。发现在吸力表面上形成的边界层产生的音调噪声可忽略不计。还观察到，压力表面上的总T-S波放大通常与测得的噪声谱良好吻合。根据本文提供的实验和预测数据，发现有效的音调噪声产生需要首先由分离的边界层放大传入的T-S波。随着迎角的增加，压力表面上压力梯度的变化会导致不稳定噪声从中等强度水平的宽带驼峰变为更高噪声强度的音调。

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  • 来源
    《Applied Acoustics》 |2013年第1期|38-48|共11页
  • 作者

    T.P. Chong; P.F. Joseph; M.J. Kingan;

  • 作者单位

    School of Engineering and Design, Brunei University, Uxbridge UB8 3PH, UK;

    Institute of Sound and Vibration Research, University of Southampton, Southampton SO17 1BJ, UK;

    Institute of Sound and Vibration Research, University of Southampton, Southampton SO17 1BJ, UK;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

    airfoil self-noise; tone noise; tollmien-schlichting waves; feedback loops;

    机译：翼型自噪声音调噪音;Tollmien-schlichting浪;反馈回路;

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