摘要
基于鸮翼的仿生翼型可用于揭示鸮翼的噪声产生机理。通过大涡模拟给出仿生翼型的流场,从中发现由前缘分离引起的两个声源分别为再附着的湍流边界层和从气泡中分离出来的涡脱落。由此可知,低雷诺数下的鸮翼宽频噪声是由湍流边界层散射导致的。之后,将被动多孔技术用于仿生翼型的后缘,在静压场中证实了多孔后缘缓解瞬态压力变化的作用。相关的噪声频谱也表明,多孔后缘具有高达10dB以上的降噪潜力,但是降噪的幅度依赖于流阻率。
An airfoil mimicking owl wings is used to determine the noise generation mechanism of silent owl. The flow field around the bionic airfoil suggests two noise sources caused by the leading-edge separation, one is the reattached turbulent boundary and the other one is the vortex shedding detached from leading-edge bubble. The reason for owl wing noise in low Reynolds number is the interaction between the turbulent boundary layer and the sharp trailing-edge of the bionic airfoil. Furthermore, as a promising means, the passive porosity technology is applied for the trailing-edge noise reduction of the airfoil. The static pressure fields around the airfoil verify that the porous trailing-edge can alleviate pressure change by the suppression of the vortex shedding and the damping of broadband turbulent boundary layer fluctuation. The relevant noise spectrum also indicates a pronounced noise reduction potential in excess of 10 dB, but in dependence on the flow resistivity. The findings of this study may be used as reference in the design of study may be used as reference in the design of silent aircraft.
出处
《吉林大学学报（工学版）》
EI
CAS
CSCD
北大核心
2016年第6期1981-1986,共6页
Journal of Jilin University:Engineering and Technology Edition
基金
国家自然科学青年基金项目(51505182)
吉林省科技发展计划项目(20160520065JH)
关键词
工程仿生学
仿生翼型
涡脱落
湍流边界层
多孔处理
后缘降噪
engineering bionics
bionic airfoil
vortex shedding
turbulent boundary layer
poroustreatment
trailing edge noise reduction
作者简介
葛长江（1981-），男，工程师，博士．研究方向：工程仿生学．E-mail：163_gongbo@163．com
