| 摘要 |
The present invention relates to a blade with a swept-back tip for the rotary wings of an aircraft, particularly a helicopter, said blade (1) being formed from successive elementary cross sections.According to the invention, with said blade (1) being subdivided into various zones, the chord length L and the offset Y'f of the aerodynamic center with respect to the feathering axis (OX), as well as the relative thickness of each elementary section, are optimized for flight within a moderate speed range.
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