Blade section for rotating wings of an aircraft

Details Blade section for rotating wings of an aircraft Blade section for rotating wings of an aircraft

1981-08-17

1983-11-22

Barefoot, Galen L.

Aeronautics and astronautics

Aircraft sustentation

Sustaining airfoils

416223R, 416242, B64C 310

Patent

active

044164343

ABSTRACT:
The present invention relates to a blade section for rotating wings of an aircraft comprising, between the leading edge and the trailing edge, a convex lower surface and an upper surface which is convex over the greater part of its length, but concave near the trailing edge. According to the invention, the upper surface of the section comprises a region of small extent, close to the leading edge but not contiguous thereto, in which the curvature is substantially constant. The invention is applicable to the improvement of the performances in maneuvering flight, while hovering and in advance flight of the aircraft.

REFERENCES:
patent: 2123096 (1938-07-01), Charpentier
patent: 2628043 (1953-02-01), Montgomery
patent: 4142837 (1979-03-01), de Simone
patent: 4314795 (1982-02-01), Dadone
Hicks et al., "Effects of Forward Contour Mod. on the Aero. Characteristics of the NACA 64, -212 Airfoil Sec.", NASA TMX-3293, Sep. 1975.

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