Abstract

The results of experimental investigations of the effect of distributed suction through a perforated section of a symmetric wing profile on the spatial development of disturbances in the boundary layer are presented. It is shown that this method of control makes it possible to reduce by ten times the intensity of natural pulsations of the boundary-layer velocity, while the disturbance intensity decreases by about 20 times, when an acoustic field is applied at the subharmonic frequency of the fundamental wave. The suction also significantly affects the mean flow up to eliminating the separation of the boundary layer near the trailing edge of the wing instead of contributing only a decrease in the intensity of high-frequency pulsations for natural and forced disturbances.

中文翻译：

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分布式抽吸对机翼轮廓扰动发展的影响

摘要

提出了通过对称机翼轮廓的穿孔部分分配吸力对边界层扰动空间发展的影响的实验研究结果。结果表明，当以声场的次谐波频率施加声场时，这种控制方法可以将边界层速度的自然脉动强度减小十倍，而干扰强度减小约二十倍。基本波。吸力还显着影响平均流量，直至消除机翼后缘附近的边界层分离，而不是仅对自然和强迫扰动造成高频脉动强度的降低。