Effect of Airfoil Aerodynamic Loading on Trailing Edge Noise Sources
Effect of Airfoil Aerodynamic Loading on Trailing Edge Noise Sources
复制标题
机翼气动载荷对后缘噪声源的影响
DOI：
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发表时间：
2005
期刊：
影响因子：
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通讯作者：
M. Roger
中科院分区：
文献类型：
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作者：
S. Moreau;M. Roger
本文对低马赫数均匀流中的工业曲面控制扩散翼型辐射的宽带自噪声进行了实验研究，并将其推广到各种气动载荷下。仪表翼型被放置在一个开放式射流消声风洞的出口处，射流宽度约为四个弦长。在测量靠近后缘的壁压波动的统计特性的同时，在远场测量声音。在弦雷诺数为2.9 × 105的翼型上收集了一组新的平均壁压数据，这提供了对雷诺数效应的一些了解。通过改变攻角从8 °到15 °，研究了具有不同统计特性的两种先前研究过的流态。它们分别对应于后缘涡脱落的近分离边界层和前缘分离引起的湍流边界层。
A previous experimental investigation of the broadband self noise radiated by an industrial cambered controlled-diffusion airfoil embedded in an homogeneous flow at low Mach number has been extended to various aerodynamic loadings. The instrumented airfoil is placed at the exit of an open-jet anechoic wind tunnel, with a jet width of about four chord lengths. Sound is measured in the far field at the same time as the statistical properties of the wall-pressure fluctuations close to the trailing edge. A new set of mean wall-pressure data has been collected on this airfoil at a chord Reynolds number of 2.9 x 105, which provides some insight on the Reynolds-number effect. Two previously investigated flow regimes with different statistical behaviors are investigated by changing the angle of attack from 8 to 15 deg. They respectively correspond to the nearly separated boundary layer with vortex shedding at the trailing edge and to the turbulent boundary layer initiated by a leading-edge separation.