Mechanisms of airfoil noise near stall conditions
Mechanisms of airfoil noise near stall conditions
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DOI：
10.1103/physrevfluids.4.123902
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发表时间：
2019-12
影响因子：
2
通讯作者：
G. Lacagnina;P. Chaitanya;T. Berk;Jung‐Hoon Kim;P. Joseph;B. Ganapathisubramani;S. Hasheminejad
中科院分区：
文献类型：
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作者：
G. Lacagnina;P. Chaitanya;T. Berk;Jung‐Hoon Kim;P. Joseph;B. Ganapathisubramani;S. Hasheminejad
本文着重研究雷诺数Re = 2×10 ~（-4）× 10 ~（-4）Re范围内翼型在大攻角下产生的噪声。目标不是模拟这种噪声源，而是了解由于分离的边界层而产生的表面压力波动的机制，然后由后缘散射。为了这个目的，我们使用同时噪声和表面压力测量除了速度测量通过热线风速仪和时间分辨粒子图像测速。对于所谓的“分离失速噪声”，除了在噪声产生中的远场噪声、表面压力和速度场之间存在明显的联系外，还确定了三种可能的机制。
The focus of this paper is on investigating the noise produced by an airfoil at high angles of attack over a range of Reynolds number Re≈2×10⁵–4×10⁵. The objective is not modeling this source of noise but rather understanding the mechanisms of generation for surface pressure fluctuations, due to a separated boundary layer, that are then scattered by the trailing edge. To this aim, we use simultaneous noise and surface pressure measurement in addition to velocimetric measurements by means of hot wire anemometry and time-resolved particle image velocimetry. Three possible mechanisms for the so-called “separation-stall noise” have been identified in addition to a clear link between far-field noise, surface pressure, and velocity fields in the noise generation.