Abstract This paper examines the possibility of controlling jet-wing interaction noise by plasma actuators. The low-frequency part of the jet installation noise is considered as produced by the diffraction of instability wave packets developing in the jet shear layer. Thus, the main idea of noise control comes to the attempt to reduce the amplitude of these wave packets near the wing trailing edge. A simplified jet-plate configuration is studied experimentally for jet Mach numbers ranging from 0.4 to 0.6. To avoid additional complications related to the control of stochastic signals in the first step, the jet is excited by a loudspeaker at a frequency corresponding to Strouhal number 0.6. Acoustic forcing generates axisymmetric instability wave in the jet shear layer, which is the object of control. The control action is implemented by a high-frequency dielectric barrier discharge (HF DBD) plasma actuator with a ring-like electrode mounted inside the nozzle near the exit. It is demonstrated that installation noise can be significantly suppressed if the plasma actuator generates instability wave with the amplitude equal to that of the excited by the loudspeaker, but in antiphase to it, and vice versa, if these instability waves are in phase, installation noise increases by about 6 dB. The obtained results support the idea that low-frequency jet-wing installation noise can be controlled in a linear framework.

中文翻译：

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等离子体致动器对激发射流的射流板相互作用噪声的主动控制

摘要 本文研究了通过等离子体致动器控制喷气机翼相互作用噪声的可能性。射流安装噪声的低频部分被认为是由在射流剪切层中发展的不稳定波包的衍射产生的。因此，噪声控制的主要思想是尝试降低机翼后缘附近这些波包的幅度。实验研究了一种简化的喷射板配置，其喷射马赫数范围为 0.4 到 0.6。为了避免在第一步中与随机信号控制相关的额外复杂性，喷射由扬声器以对应于 Strouhal 数 0.6 的频率激发。声强迫在射流剪切层中产生轴对称不稳定波，这是控制的对象。控制动作由高频介质阻挡放电 (HF DBD) 等离子体执行器实现，该执行器在出口附近的喷嘴内安装了一个环形电极。结果表明，如果等离子致动器产生振幅与扬声器激发的振幅相等但与其反相的不稳定波，则可以显着抑制安装噪声，反之亦然，如果这些不稳定波同相，则安装噪声增加约 6 dB。获得的结果支持低频喷气机翼安装噪声可以在线性框架中控制的想法。结果表明，如果等离子致动器产生振幅与扬声器激发的振幅相等但与其反相的不稳定波，则可以显着抑制安装噪声，反之亦然，如果这些不稳定波同相，则安装噪声增加约 6 dB。获得的结果支持低频喷气机翼安装噪声可以在线性框架中控制的想法。结果表明，如果等离子致动器产生振幅与扬声器激发的振幅相等但与其反相的不稳定波，则可以显着抑制安装噪声，反之亦然，如果这些不稳定波同相，则安装噪声增加约 6 dB。获得的结果支持低频喷气机翼安装噪声可以在线性框架中控制的想法。