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Airfoil-Gust Interactions in Transonic Flow

机译：跨动力流动的翼型 - 阵风相互作用

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Leading edge noise is a significant broadband noise source in aircraft engines, and is the primary broadband noise mechanism in outlet guide vane noise in turbofans, and broadband rotor wake interaction noise in contra-rotating open rotor engines. Previous authors have studied the effects of various aspects relating to this noise source, including airfoil geometry effects, cascade effects, and Mach number effects. However, previous literature has not addressed the effects on the noise due to locally supersonic regions that might be present in the mean flow around the rotor blades. The current work uses computational aeroacoustic methods to investigate the effects of locally supersonic regions on the noise due to airfoil-gust interactions. An established computational aeroacoustics code has been extended to give stable predictions in supersonic regions with a localized artificial diffusivity method. Initial results of a NACA 0012 airfoil in M = 0.8 flow interacting with oncoming vortical waves are shown, alongside results for a NACA 0006 airfoil in M = 0.5 flow at a 6° angle of attack. The changes to the noise and the underlying mechanisms are discussed for both cases, including additional noise sources caused by the supersonic region.
机译：前沿噪声是飞机发动机中的显着宽带噪声源，是涡轮机的出口导向叶片噪声中的主要宽带噪声机制，宽带转子唤醒相互作用噪声在旋转旋转的开口转子发动机中。以前的作者研究了各个方面与该噪声源有关的各个方面的影响，包括翼型几何效应，级联效应和马赫数效应。然而，先前的文献没有解决由于局部超音子区域引起的噪声的影响，这些局部超音区可能存在于转子叶片周围的平均流动中。目前的工作采用计算的气动声学方法来研究局部超声区域对由于翼型 - 阵风相互作用引起的噪声的影响。已经延长了建立的计算空气声学代码，以在具有局部人工扩散性方法的超音速区域提供稳定的预测。显示NACA 0012翼型的初始结果在M = 0.8流中与迎面而来的涡流相互作用，与M = 0.5的NaCa 0006翼型以6°发作角度一起进行NaCa 0006翼型。两种情况讨论了对噪声和底层机制的改变，包括由超音子区域引起的额外噪声源。

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