Suppression of Tonal Trailing-Edge Noise From an Airfoil Using a Plasma Actuator

被引:41
|
作者
Inasawa, Ayumu [1 ]
Ninomiya, Chiho [1 ]
Asai, Masahito [1 ]
机构
[1] Tokyo Metropolitan Univ, Tokyo 191, Japan
关键词
SEPARATION CONTROL; FLOW-CONTROL; TONES;
D O I
10.2514/1.J052203
中图分类号
V [航空、航天];
学科分类号
08 ; 0825 ;
摘要
Suppression control of tonal noise generation at an airfoil trailing edge was conducted using a plasma actuator for a NACA0012 airfoil at a 2-deg angle of attack and at a Reynolds number 2.2 x 10(5) where the acoustic feedback responsible for the trailing-edge noise generation occurs in the pressure-side boundary layer. To minimize the possible interference of electrode installation in the boundary-layer stability a specially designed actuator with flush-mounted electrode configuration was employed. It was found that when the plasma actuator was installed at 55-60% chord location on the pressure surface a surface flow induced by the actuator stabilizes the downstream boundary-layer most significantly to suppress the strong growth of instability waves, which is responsible for the occurrence of the acoustic feedback. Consequently, suppression of the tonal trailing-edge noise was successfully achieved.
引用
收藏
页码:1695 / 1702
页数:8
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