ROTOR BLADE FOR HIGH-SPEED GYRODYNE AIRCRAFT Russian patent published in 2011 - IPC B64C27/32 B64C27/46 

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering, particularly to gyrodyne aircraft rotor blade. Rotor blade is configured to make blade chord increase from blade root to blade main section, and decrease from the latter to rotor blade tip. Note here that the blade can be configured so that blade chord increases within the limits of the blade main section to maximum chord and, then decreases within the same limits outward from the maximum rotor blade chord. It is possible also to configure the blade so that maximum chord lies between 65% R and 75% R of rotor blade span defined from blade rotational axis to distal end of blade tip section to determine elliptical distribution.

EFFECT: gyrodyne aircraft rotor blade for flight at speeds over 250 knots.

30 cl, 12 dwg