Near-field aeroacoustic characteristics of a stalled NACA 0012 aerofoil
Near-field aeroacoustic characteristics of a stalled NACA 0012 aerofoil
复制标题
失速 NACA 0012 翼型的近场气动声学特性
DOI：
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发表时间：
2019
期刊：
影响因子：
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通讯作者：
M. Azarpeyvand
中科院分区：
文献类型：
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作者：
Y. Mayer;B. Zang;M. Azarpeyvand
失速和分离噪声可能是旋转叶片（诸如风力涡轮机、螺旋桨和风扇等）的噪声排放的主要贡献者。因此，本文通过实验研究了分离边界层对近场流场结构、湍流表面压力脉动统计以及噪声辐射的影响。给出了失速前和失速后流场的静压分布和边界层剖面。大的表面压力脉动谱增加已被测量，和表面压力脉动自相关宽度增加了一个数量级的失速期间已经建立。此外，高度相干的展向结构已被证明会影响流体动力场，并对分离边界层的对流速度变化进行了评估。
Stall and separation noise can be major contributors to the noise emission of rotating blades, such as wind turbines, propellers and fans among others. Hence, this paper experimentally investigates the effects a separated boundary layer has on near-field flow structures, on turbulent surface pressure fluctuation statistics, and therefore on noise radiation. Static pressure distributions and boundary layer profiles are presented to characterize the present flow fields preand post-stall. Large surface pressure fluctuation spectra increases have been measured, and surface pressure fluctuation autocorrelation width increases by one order of magnitude during stall have been established. Additionally, highly coherent spanwise structures have been shown to influence the hydrodynamic field and changes in the convection velocity have been assessed for separated boundary layers.