Patent ID: 9027883
Filing Date: 2015-05-12
Classification: B64C,Y10T

Abstract:
1. An aircraft comprising an elongate shock control fairing mounted on the upper surface of a junction between the aircraft fuselage and wing, the fairing comprising a fixed outer surface arranged to extend between the fuselage and the upper surface of the wing, and the length of the fairing extending along a chordwise direction of the aircraft wing root, wherein the curvature of the outer surface of the fairing varies along the length of the fairing, such that the fairing comprises a fore-region having concave curvature, a mid-region having convex curvature, and an aft-region having neutral curvature, and wherein the area of the cross-sectional profile of the fairing generally continually increases from the fore-region of the fairing towards the mid-region of the fairing, reaching a maximum area in the mid-chord region of the wing root, and then generally decreases from the mid-region of the fairing towards the aft-region of the fairing, the fairing being shaped such that the maximum area of the cross-sectional profile of the fairing is at a location within the mid-chord region of the wing root which is substantially proximal to a location on the surface of the aircraft at which a shock would be expected to develop without the fairing during transonic flight.