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.
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