Reynolds number effects on tonal noise generation from an airfoil

XU Siwei; LI Weipeng

doi:10.7638/kqdlxxb-2018.0123

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Reynolds number effects on tonal noise generation from an airfoil

更新时间：2026-05-28

- Reynolds number effects on tonal noise generation from an airfoil
- Vol. 37, Issue 3, Pages: 382-392(2019)
- 作者机构：
  
  上海交通大学航空航天学院,上海,200240
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2018.0123
  CLC： V211.3
- Published：2019
- 稿件说明：
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许思为, 李伟鹏. 雷诺数对机翼尾缘噪声的影响[J]. 空气动力学学报, 2019, 37(3): 382-392.

XU Siwei, LI Weipeng. Reynolds number effects on tonal noise generation from an airfoil[J]. 2019, 37(3): 382-392.
许思为, 李伟鹏. 雷诺数对机翼尾缘噪声的影响[J]. 空气动力学学报, 2019, 37(3): 382-392. DOI： 10.7638/kqdlxxb-2018.0123.

XU Siwei, LI Weipeng. Reynolds number effects on tonal noise generation from an airfoil[J]. 2019, 37(3): 382-392. DOI： 10.7638/kqdlxxb-2018.0123.

摘要

采用二维直接数值模拟，研究了雷诺数对NACA0015翼型尾缘噪声特征和噪声机理的影响。研究结果表明翼型尾缘噪声机理和频谱特征随雷诺数变化而显著不同，在中等雷诺数（

=5×10

）条件下，吸力面与压力面的脱涡结构独自诱导发声，在频谱上表现为在多个不同的窄带峰值频率，利用线性稳定性分析，表明脱涡结构频率与不稳定T-S波的增长频率一致，尾缘脱涡结构的生成和噪声激励之间存在闭环反馈环机制，且闭环反馈环机制同时存在于机翼的压力面与吸力面。在低雷诺数（

=1×10

）条件下，仅观测到的单一的窄带频率，其原因与剪切层的固有不稳定性直接相关。

Abstract

The tonal noise generation from a NACA0015 airfoil at a low (

=1×10

) and a moderate (

=5×10

) Reynolds number is studied by performing two-dimensional direct numerical simulations. The effects of Reynolds number result in distinguishing features on the acoustic fields and thus the spectra. For the moderate Reynolds number cases

the vortex shedding on the suction and pressure side of the airfoil contributes separately to the generation of the acoustic waves

corresponding to an individual hump with different discrete frequencies in the acoustic spectra. A linear stability analysis is used to clarify the relation betwe

en the formation of vortices with the growth of unstable Tollmien-Schlichting (T-S) waves. Results suggest that the single tone observed in the low Reynolds number cases is probably associated with the inherent hydrodynamic instability of the boundary layer

whereas the multiple tones in the moderate Reynolds number cases are considered to be associated with a feedback loop mechanism between the formation of vortices and the excitation of acoustic disturbances. Feedback loops actually exist on both sides of the airfoil rather than just on the pressure side or on the suction side of the airfoil.

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