Trailing edge noise from hovering rotors
Trailing edge noise from hovering rotors
复制标题
悬停旋翼产生的后缘噪音
DOI：
10.2514/3.51176
复制
发表时间：
1980
期刊：
影响因子：
2.5
通讯作者：
A. George
中科院分区：
文献类型：
--
作者：
Y. N. Kim;A. George
本文提出了一种计算悬停旋翼尾缘与对流湍流涡相互作用产生的高频宽带噪声的方法。每个叶片的后缘噪声被模拟为带有展向载荷修正的点偶极子噪声。通过将该概念应用于运动介质中的静止翼型来检验该点偶极近似，结果良好。为了估计点偶极子的强度，使用Amiet的后缘噪声理论。该方法专门应用于叶片边界层湍流，并与入射大气湍流噪声进行比较。结果表明，这两种机制的相对重要性与来流和边界层湍流的强度和长度尺度的大小有关。结果往往低于一些可用的实验数据，表明在这些实验中，其他宽带噪声源比边界层后缘噪声更强。该方法也适用于其他叶片湍流干扰机制，如局部失速和叶尖噪声。
A method has been developed to predict the high frequency broadband noise due to the interaction of convecting turbulent eddies with the trailing edges of a hovering rotor. The trailing edge noise from each blade was modeled as point dipole noise with spanwise loading corrections. This point dipole approximation was checked by applying the concept to a stationary airfoil in a moving medium with excellent results. In order to estimate the strength of the point dipole, the trailing edge noise theory of Amiet was used. The method was applied specifically to blade boundary layer turbulence and compared to incident atmospheric turbulence noise. The results indicate that the relative importance of these two mechanisms is related to the magnitudes of the intensity and of the length scales of the inflow and boundary layer turbulence. The results tend to fall below some available experimental data indicating that in those experiments other broadband noise sources were stronger than boundary layer-trailing edge noise. The approach which was developed is also applicable to other blade-turbulence interaction mechanisms such as local stall and tip noise.
747天桥？
DOI：
10.1038/oby.2009.209
发表时间：
2009
期刊：
Obesity (Silver Spring, Md.)
影响因子：
--
作者：
Bergman,RichardN
通讯作者：
Bergman,RichardN