Patent ID: 6116857
Filing Date: 2000-09-12
Classification: B64C

Abstract:
A blade for an aircraft rotating aerofoil, comprising an aerodynamically profiled main part extending, more than fifty percent of the blade, between a leading edge and a trailing edge, and, along the blade span, between a footing part provided with a blade root for its connection to a rotor hub rotating about a rotor axis of rotation, and a blade tip, at its free end, wherein the aerodynamically profiled main part includes an external end part, relative to the rotor axis, and adjacent to the blade tip, the aforesaid end part extending along the span over a distance of at least 0.2 R, where R is the rotor radius measured between the rotor axis of rotation and the blade tip, and the aforesaid end part being rear cambered over a distance along the span of at least 0.15 R, the aforesaid aerodynamically profiled main part comprising also a front cambered part, which is immediately adjacent to the inside of the rear cambered end part, the aerodynamically profiled main part comprising in addition a progressively increasing chord portion which is extended by a progressively decreasing chord portion along the span in the direction of the blade tip.