| 摘要 |
The present invention relates to a method for reducing the blade-vortex interaction noise of rotary wings. According to the invention: at least one valueΨo of the azimuth of the blades (1) is determined, for which value said blades shed tip vortices giving rise to a peak intensity of noise; a trailing edge flap (2) is disposed on each blade (1), the former generating an auxiliary vortex (11), parallel to the tip vortex (10) and attached to a blade section (8) lying between the blade section (7) around which the speed circulation is a maximum and the tip section (3) of said blade; and a deflection is applied to each of said flaps (2) such that, for said valueΨo, the speed circulation around said blade section (8) is a specified fraction of the maximum speed circulation.
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