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Effects of porous trailing edge on aerodynamic noise characteristics
International Journal of Aeroacoustics ( IF 1 ) Pub Date : 2020-06-01 , DOI: 10.1177/1475472x20937941
Minghui Zhang 1 , Tze Pei Chong 2
Affiliation  

The objective of this work is to investigate the effect of the porous trailing edge on the aeroacoustics performance of the NACA 65(12)-10 aerofoil. The motivation behind this study is to investigate the effect of the porous parameters to explore the noise control concepts. Experimental testing in an aeroacoustics open jet wind tunnel was performed at chord-based Reynolds numbers between 0.2 and 0.6 million, and effective angles of attack at ±1.7 degree, including at 0 degrees. The porous trailing edge at porosity 30% with different holes diameters and the length of these porous trailing edges are used in the acoustic experiments. The study reveals that the level of the reduction of the broadband noise becomes larger as the diameter of the holes decreases and the length of the porous trailing edge increases at lower Reynolds numbers. Bluntness-induced tone noise is produced at high Reynolds number. Meanwhile, the porous trailing edge can suppress the laminar instability noise at the middle and low frequency regions.

中文翻译:

多孔后缘对气动噪声特性的影响

这项工作的目的是研究多孔后缘对 NACA 65(12)-10 翼型气动声学性能的影响。这项研究背后的动机是研究多孔参数对探索噪声控制概念的影响。在气动声学开放式喷射风洞中进行了实验测试,基于弦的雷诺数介于 0.2 和 60 万之间,有效攻角为 ±1.7 度,包括 0 度。在声学实验中使用具有不同孔径的孔隙率为 30% 的多孔后缘和这些多孔后缘的长度。研究表明,随着孔的直径减小和多孔后缘长度在较低雷诺数下增加,宽带噪声的降低水平变得更大。在高雷诺数下会产生钝感音调噪声。同时,多孔后缘可以抑制中低频区域的层流不稳定噪声。
更新日期:2020-06-01
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