Suppression of Tonal Trailing-Edge Noise From an Airfoil Using a Plasma Actuator
Suppression of Tonal Trailing-Edge Noise From an Airfoil Using a Plasma Actuator
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DOI：
10.2514/1.j052203
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发表时间：
2013-07
期刊：
影响因子：
2.5
通讯作者：
A. Inasawa;Chiho Ninomiya;M. Asai
中科院分区：
文献类型：
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作者：
A. Inasawa;Chiho Ninomiya;M. Asai
采用等离子体激励器对NACA 0012翼型在2 °攻角和雷诺数2.2×105下进行了翼型后缘音调噪声产生的抑制控制，其中导致后缘噪声产生的声反馈发生在压力侧边界层中。为了减小电极安装对边界层稳定性的可能干扰，采用了一种特殊设计的嵌入式电极结构的致动器。结果表明，当等离子体激励器安装在压力面上55-60%弦长处时，激励器诱导的表面流动对下游边界层的稳定作用最显著，从而抑制了不稳定波的强烈增长，而不稳定波是声反馈发生的原因。因此，成功地实现了音调后缘噪声的抑制。
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 2.2×105 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.