The effect of acoustic forcing on an airfoil tonal noise mechanism

被引：5
|
作者：
Schumacher, Karn L. [1 ]
Doolan, Con J. [1 ]
Kelso, Richard M. [1 ]
机构：
[1] Univ Adelaide, Sch Mech Engn, Adelaide, SA 5005, Australia
来源：
JOURNAL OF THE ACOUSTICAL SOCIETY OF AMERICA | 2014年 / 136卷 / 02期
关键词：
TONES; AEROFOIL; FLOW; GENERATION;
D O I：
10.1121/1.4885485
中图分类号：
O42 [声学];
学科分类号：
070206 ; 082403 ;
摘要：
The response of the boundary layer over an airfoil with cavity to external acoustic forcing, across a sweep of frequencies, was measured. The boundary layer downstream of the cavity trailing edge was found to respond strongly and selectively at the natural airfoil tonal frequencies. This is considered to be due to enhanced feedback. However, the shear layer upstream of the cavity trailing edge did not respond at these frequencies. These findings confirm that an aeroacoustic feedback loop exists between the airfoil trailing edge and a location near the cavity trailing edge. (C) 2014 Acoustical Society of America
引用
收藏
页码：EL78 / EL83
页数：6
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