雷诺数和射流噪声标度

IF 1.2 4区工程技术 Q3 ACOUSTICS International Journal of Aeroacoustics Pub Date : 2023-09-06 DOI:10.1177/1475472x231199188

Aharon Z. Karon, K. K. Ahuja

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引用次数: 0

摘要

雷诺数和马赫数是用于确定气动流动相似性的经典量。现有关于雷诺数对射流噪声作用的研究结果不一致，这让人怀疑喷嘴直径有多小才能使经典的射流噪声标度定律成立。因此，为解决这一问题进行了系统的研究。使用介于0.4和0.8之间的马赫数变化以及0.25、0.5和2英寸的喷嘴出口直径来调整射流的雷诺数。当对喷气噪声测量值进行归一化时，在整个雷诺数范围内观察到光谱坍塌。研究发现，雷诺数对射流噪声没有显著影响，射流噪声可以从最小的喷嘴缩放到较大的喷嘴。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

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Reynolds number and jet noise scaling

The Reynolds number and Mach number are classical quantities used to determine the similarity of aerodynamic flows. Existing studies on the role of Reynolds Number on jet noise show inconsistent results, casting doubt on how small a nozzle diameter can be for the classical jet noise scaling laws to hold. A systematic study was therefore undertaken to resolve this issue. The Reynolds number of jet flows was adjusted using a Mach number variation between 0.4 and 0.8, and nozzle-exit diameters of 0.25, 0.5, and two inches. When the jet noise measurements were normalized, spectral collapse was observed for the spectra across the whole Reynolds number range. It was found that the Reynolds number does not have a significant effect on jet noise, and jet noise can be scaled from even the smallest of nozzle to larger nozzles.

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来源期刊

International Journal of Aeroacoustics ACOUSTICS-ENGINEERING, AEROSPACE

CiteScore

2.10

自引率

10.00%

发文量

审稿时长

>12 weeks

期刊介绍： International Journal of Aeroacoustics is a peer-reviewed journal publishing developments in all areas of fundamental and applied aeroacoustics. Fundamental topics include advances in understanding aeroacoustics phenomena; applied topics include all aspects of civil and military aircraft, automobile and high speed train aeroacoustics, and the impact of acoustics on structures. As well as original contributions, state of the art reviews and surveys will be published. Subtopics include, among others, jet mixing noise; screech tones; broadband shock associated noise and methods for suppression; the near-ground acoustic environment of Short Take-Off and Vertical Landing (STOVL) aircraft; weapons bay aeroacoustics, cavity acoustics, closed-loop feedback control of aeroacoustic phenomena; computational aeroacoustics including high fidelity numerical simulations, and analytical acoustics.