Blade section for rotating wings of an aircraft
Patent 4416434 Issued on November 22, 1983. Estimated Expiration Date: 
August 17, 2001. Estimated Expiration Date is calculated based on simple USPTO term provisions. It does not account for terminal disclaimers, term adjustments, failure to pay maintenance fees, or other factors which might affect the term of a patent.
August 17, 2001. Estimated Expiration Date is calculated based on simple USPTO term provisions. It does not account for terminal disclaimers, term adjustments, failure to pay maintenance fees, or other factors which might affect the term of a patent.Patent References 2123096 2628043 Helicopter blade Advanced airfoils for helicopter rotor application Patent #: 4314795 InventorsAssigneeApplicationNo. 06/293683 filed on 08/17/1981US Classes:244/35R, Sustaining airfoils416/223R, SPECIFIC BLADE STRUCTURE (E.G., SHAPE, MATERIAL, ETC.)416/242Reverse curve surfaceExaminersPrimary: Barefoot, Galen L.Attorney, Agent or FirmInternational ClassesB64C 27/32 (20060101)B64C 27/467 (20060101) Foreign Application Priority Data1980-09-24 FRAbstractThe 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.Other References
Field of SearchHelicopter or auto-rotating wing sustained, i.e., gyroplanes | |
