U.S. Patent Specifications

Aircraft Engineering and Aerospace Technology

ISSN: 0002-2667

Publication date: 1 November 1955

Abstract

A lifting surface or body, such as an aeroplane wing, adapted to be driven through fluids, such as air; said lifting body having a plan view form such that the leading and trailing edges of said plan view form are swept aft with respect to a vertical plane transverse to the plane of symmetry or longitudinal axis of the said lifting body; said lifting body having a structure within the said plan view form incorporating root, tip and one or more intermediate aerofoil sections specifically shaped wherein the radii of curvature of the leading and trailing edges and the chordwise positions of the maximum thickness of said aerofoil sections vary spanwise from root to tip in a progressive and proportionate manner forming smooth surface contours of and between the said aerofoil sections; whereby the structure of the said root section consists of the following three features: one, a sharp leading edge formed by an edge radius smaller than the edge radius of the trailing edge of feature two following; two, a blunt trailing edge formed by an edge radius larger than the edge radius of the leading edge of feature one preceding; and three, a position of maximum thickness, defined in per cent of the aerofoil section chord, closest to the trailing edge; whereby the structure of the said tip section consists of the following three features: one, a blunt leading edge formed by an edge radius larger than the edge radius of the trailing edge of feature two following; two, a sharp trailing edge formed by an edge radius smaller than the edge radius of the leading edge of feature one preceding; and three, a position of maximum thickness, defined in per cent of the aerofoil section chord, closest to the leading edge; and whereby the structure of the said one or more intermediate aerofoil sections between said root and tip sections have radii of curvature of their leading and trailing edges, and positions of maximum thickness, defined in per cent of the aerofoil section chord, progressively and proportionately altered in a manner whereby smooth surface fairing of and between the said aerofoil sections at root and tip with the said intermediate sections thereof is provided.

Citation

(1955), "U.S. Patent Specifications", Aircraft Engineering and Aerospace Technology, Vol. 27 No. 11, pp. 390-391. https://doi.org/10.1108/eb032630

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Publisher

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MCB UP Ltd

Copyright © 1955, MCB UP Limited

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