Progress of research on airfoil trailing edge tonal noiseat low-moderate Reynolds number and its control
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摘要: 基于国内外研究成果，本文总结了中/低雷诺数下翼型后缘纯音噪声的物理机制与主/被动控制的研究现状，阐述了目前该研究还需回答与解决的部分问题，并对可能的新研究思路与方法进行了展望。在物理机制方面，边界层内声反馈和后缘涡脱落被公认为中/低雷诺数下翼型后缘纯音噪声的两种主要发声机制。前者由T–S不稳定波散射噪声向上游传播、在边界层与翼型后缘之间形成，产生的纯音噪声具有典型“阶梯状”离散频谱特性；后者涡脱落机制由翼型尾流整体不稳定性引起，纯音噪声具有单一频率特性。两种发声机制之间如何竞争以及噪声频率如何选择等问题仍未完全解决。在研究方法方面，主要采用线性稳定性分析、风洞实验测量和DNS/LES数值模拟等研究方法。由于现有研究的翼型较为单一，所得结果无法满足翼型低噪声设计的需求。在噪声控制方面，被动控制方法多采用翼型前/后缘锯齿、多孔材料和柔性壁面，主动控制方法多采用表面吹/吸气和等离子体技术，但如何利用机理分析来有效抑制翼型后缘纯音噪声方面，还有较多可改进之处。Abstract: This paper summarizes the research on the airfoil trailing edge (TE) tonal noise at low-moderate Reynolds number. Also included are the unsolved problems and their prospected research ideas and roads. The acoustic feedback loop and the vortex shedding are considered to be the two main mechanisms for the generation of airfoil TE tones. The former is formed between the boundary layer and the TE and is associated with the ladder-type discrete tones, while the latter contributes to the single-frequency tonal noise due to global instability. The airfoil TE noise is investigated experimentally in the open/closed wind tunnels and numerically through DNS/LES methods. The development of the T–S waves in the boundary layer is calculated using the linear stability theory, and the vortex shedding is analyzed using the concept of absolute/convective instability. Passive control methods, such as the airfoil leading edge or TE serrations, porous material, and morphing surface, are applied to attenuate the airfoil TE tonal noise. Two main active control strategies are the applications of blowing/suction and the plasma technique. Though the airfoil TE tone at low-moderate Reynolds number has been studied for half a century, some issues still need to be answered, and future development is also prospected.
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图 5 形成翼型后缘单频纯音噪声的涡脱落机制
Figure 5. Schematic mechanism of vortex shedding for single frequency tonal noise generation
图 9 采用多孔材料翼型和变形副翼控制噪声
Figure 9. The use of porous material and morphing TE for the airfoil TE noise control
图 13 风洞闭口实验段内的翼型模型及安装示意图
Figure 13. Airfoil model and its test setup in a closed wind tunnel
表 1 边界层层流分离泡位置随来流雷诺数的变化[23]
Table 1. Laminar separation bubble （LSB） locations on the suction and pressure sides[23]
α Re Suction Side Pressure Side 2° 144000 52%c ～ 80%c 84%c ～ 100%c 2° 180000 53%c ～ 74%c 82%c ～ 100%c 2° 216000 54%c ～ 69%c 80%c ～ 100%c 2° 252000 55%c ～ 66%c 82%c ～ 100%c 2° 288000 57%c ～ 64%c 85%c ～ 100%c 
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