Aircraft structures

Claim 1

An aircraft comprising a narrow delta planform fuselage whose longitudinal section contours form low drag-high lift aerodynamic airfoils, said delta planform fuselage carrying two comparatively small span shoulder type wings at the level of the upper surface of the fuselage in tandem and in cascade, the rear wing being of larger span than the forward wing, the mean aerodynamic chords of the wings forming zero to small negative angles of incidence in respect of the zero-lift angle of incidence of the fuselage mean aerodynamic chord, the rear wing of the aircraft being so constructed that the side and top surfaces of the fuselage blend smoothly with the upper surface of the rear wing while the surfaces of the fuselage below the rear wing meet with normal continuity with the under surface of the rear wing, the wings being positioned in tandem and in cascade so as to cause generation of additional air flow momentum above the fuselage rearward of the forward wing and above the central portion of the rear wing; a twin tail located at the rear of the fuselage with a trailing edge elevator located between the twin tail and forming the trailing edge of the fuselage; the trailing edge of the rear and forward wings being substantially at right angles to the longitudinal axis of the aircraft and said delta fuselage carrying a power plant system above the upper surface of the fuselage and as far as stability requirements permit rearward in respect of the centre of gravity of the aircraft.