| 摘要 |
The invention relates to a blade end for rotary wing of an aircraft, whose span is between 5 and 15% of the span of said blade. According to the invention, this blade end is charaterized in that, between points A and B', there is a stagger which, measured parallel to the span of the blade, is between 5 and 25% of the chord of the profile of the blade adjacent said blade end and in that the leading edge line of said blade end is curvilinear and such that its angle of sweep phi varies progressively and continuously from a low value phi o near the blade, of between 0 DEG and 30 DEG , up to a high value phi E towards the outside of the blade, of between 60 DEG and 90 DEG . The invention leads to increased performances and to a reduction in the noise level of rotary wings.
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