Abstract: An aircraft includes a central wing accommodating passengers and/or freight and two lateral wings that pivot on the central wing about respective axes of rotation. The various wings obey the following geometric characteristics: 0.3×Long<Larg<Long, 0.11×Long<Haut<0.25×Long, Env>1.4×Long, wherein Larg being the distance between the two axes, Long being the length of the central wing, Haut being the height of the central wing, Env being the wingspan of the aircraft. The axes of rotation are inclined by an angle relative to the vertical axis of the aircraft such that the lateral pivot from rear to front and vice versa so as to come closer to, or deploy on either side from, the fuselage.

Abstract: An aeroplane includes a fuselage having a pair of hydrofoils providing hydrodynamic lift and stabilization arranged in the form of an inverted V. The junction between each hydrofoil and fuselage is situated forward the center of gravity of the aeroplane. The distance separating the junction between each hydrofoil and the fuselage, with respect to the center of gravity of the aeroplane is comprised between 0 and 170% of the mean aerodynamic chord of the main wing of the aeroplane, preferably between 20% and 135%. Each hydrofoil is inclined downwards, from its leading edge in the direction of its trailing edge. The straight line connecting these two edges form, a nominal pitch angle comprised between 2 and 12°, preferably between 6 and 8°. A part of the hydrofoil is located beneath a horizontal tangential plane of the aeroplane; each hydrofoil has a flexible intermediate section allowing the hydrofoil to flex upwards.

Abstract: An aeroplane includes a fuselage having a pair of hydrofoils providing hydrodynamic lift and stabilization arranged downwards in the form of an inverted V. The junction between each hydrofoil and the fuselage is situated forward from the centre of gravity of the aeroplane. The distance separating the junction between each hydrofoil and the fuselage, with respect to the centre of gravity of the aeroplane is comprised between 0 and 170% of the mean aerodynamic chord of the main wing of the aeroplane, preferably between 20% and 135%. Each hydrofoil is inclined downwards, from its leading edge in the direction of its trailing edge. The straight line connecting these two edges form, a nominal pitch angle comprised between 2 and 12°, preferably between 6 and 8°. The part of the hydrofoil located beneath the tangential plane is situated forward from the centre of gravity.