Downstream porosity for the reduction of turbulence-aerofoil interaction noise
Downstream porosity for the reduction of turbulence-aerofoil interaction noise
复制标题
用于减少湍流-机翼相互作用噪声的下游孔隙度
DOI：
10.1016/j.jsv.2022.117324
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发表时间：
2022
影响因子：
4.7
通讯作者：
Palleja-Cabre S
中科院分区：
文献类型：
--
作者：
Palleja-Cabre S
本文主要是关于利用位于机翼前缘下游的孔隙度来减少湍流相互作用噪声的实验研究。与将其直接定位在产生大部分升力的前缘处相比，将孔隙率定位在前缘下游已被证明有利于减少空气动力性能损失（Ocker 等人，2021）。将具有下游孔隙率的平板上的噪声测量值与串联配置的两个平板的情况进行比较。在这两种情况下，降噪谱均在无量纲频率 f l d/U c= n 处呈现强降噪峰值，其中 l d 为前缘与下游边缘之间的距离，U c 为对流速度，n 为整数。为了解释这种行为，需要存在一种机制，在相互作用过程中引入 180∘ 的相移。在本文中，我们认为这种相移的根源是由于前缘产生的二次涡度。本文的另一个重要发现是，整体噪声的降低是由于弦的有效缩短，其中大部分辐射是由多孔部分上游的平板部分产生的，导致辐射普遍较弱。这些机制之前都没有在文献中报道过。该论文最后对包含下游孔隙度的薄翼型进行了噪声测量，总体噪声降低了高达 2.8 dB。
This paper is a predominantly experimental study into the use of porosity located downstream of an aerofoil leading edge for the reduction of turbulence interaction noise. Locating the porosity downstream of the leading edge has been shown to be beneficial in reducing the aerodynamic performance penalty compared with locating it directly at the leading edge (Ocker et al., 2021), where most of the lift is generated. Noise measurements on a flat plate with downstream porosity are compared against the case of two flat plates in a tandem configuration. In both cases, the noise reduction spectra exhibit peaks of strong noise reduction at non-dimensional frequencies of f l d/U c= n, where l d is the distance between the leading edge and the downstream edge, U c is the convection velocity and n is an integer. To explain this behaviour requires a mechanism to be present in which a phase shift of 180∘ is introduced in the interaction process. In the paper we argue that the origin of this phase shift is due to secondary vorticity generated at the leading edge. Another key finding of this paper is that overall noise reductions are due to an effective shortening of the chord in which most of the radiation is produced by the section of the flat plate upstream of the porous section, leading to generally weaker radiation. Neither of these mechanisms have been reported previously in the literature. The paper concludes with noise measurements on a thin aerofoil with downstream porosity included, in which overall noise reductions of up to 2.8 dB are achieved.
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影响因子：
4.7
作者：
R. Zamponi;S. Satcunanathan;S. Moreau;D. Ragni;M. Meinke;W. Schröder;C. Schram
通讯作者：
R. Zamponi;S. Satcunanathan;S. Moreau;D. Ragni;M. Meinke;W. Schröder;C. Schram
短、高面积比 90 度弯曲扩散器被动流量控制的参数研究
DOI：
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发表时间：
2008
期刊：
影响因子：
--
作者：
T. Chong;P. Joseph;P. Davies
通讯作者：
P. Davies
多孔处理降低翼型湍流冲击噪声的实验研究
DOI：
--
发表时间：
2019
期刊：
Advanced Courses
影响因子：
--
作者：
R. Zamponi;D. Ragni;N. Wyer;C. Schram
通讯作者：
C. Schram
DOI：
--
发表时间：
2017
期刊：
影响因子：
--
作者：
W. Blake
通讯作者：
W. Blake
DOI：
10.2514/6.2021-2192
发表时间：
2021
期刊：
AIAA AVIATION 2021 FORUM
影响因子：
--
作者：
C. Ocker;Felix Czwielong;T. Geyer;P. Chaitanya;M. Merkel;S. Becker
通讯作者：
S. Becker