Abstract: An aircraft includes a fuselage and takeoff and landing wings that are extended at takeoff and landing and serve as the main aerodynamic elements producing the lift. The takeoff and landing wings are in a retracted position in cruising flight to attain a minimum possible drag coefficient of the aircraft and, as a result, reduce fuel requirements in the cruising configuration significantly. When retracted, the takeoff and landing wings are integrated compactly into the fuselage surface. The retracted takeoff and landing wings are fixed in position by retracted position locks of the fuselage. A takeoff and landing wing has a turbine blade profile in cross-section. A takeoff and landing wing has longitudinal rows of slots simulating the operation of a slat and a two-slot flap. The slots are closed with shutters on the outer side of the wing.

Abstract: The aircraft includes a fuselage, horizontal front and tail empennages and take-off and landing wings, which wings are jointed to the fuselage by means of attachment joints, the axes of which are situated above the fuselage central line along the longitudinal axis of symmetry thereof so that the take-off and landing wings are arranged below the attachment joints along the longitudinal axis of symmetry of the fuselage. The outer surface of the wings is the extension of the outer surface of the fuselage and in a stow position the take-off and landing wings cover at least 30% of the fuselage surface area between the horizontal front and tail empennages.

Abstract: The idea of the invention is that the aircraft comprises takeoff and landing wings that are the main aerodynamic elements producing a lift at all stages of takeoff and landing. In cruising flight, the takeoff and landing wings take the flight configuration of a cruise missile to reduce the drag coefficient of the aircraft to a minimum possible and, as a result, save considerable quantities of fuel in the cruising configuration. Each takeoff and landing wing has an invariable cross-section and is provided with two rows of slots to improve resistance to the loss of airflow on the outer surface of the wing. The slots on the outside of the takeoff and landing wing are closed with flaps. This wing design is capable of generating a lift at angles of attack ranging from 1° to 90°. The takeoff and landing wings of the aircraft are unfolded at takeoff. As the aircraft climbs, the takeoff and landing wings are lowered into the folded position with a rise in the basic speed.

Abstract: An aircraft includes a fuselage and takeoff and landing wings that are extended at takeoff and landing and serve as the main aerodynamic elements producing the lift. The takeoff and landing wings are in a retracted position in cruising flight to attain a minimum possible drag coefficient of the aircraft and, as a result, reduce fuel requirements in the cruising configuration significantly. When retracted, the takeoff and landing wings are integrated compactly into the fuselage surface. The retracted takeoff and landing wings are fixed in position by retracted position locks of the fuselage. A takeoff and landing wing has a turbine blade profile in cross-section. A takeoff and landing wing has longitudinal rows of slots simulating the operation of a slat and a two-slot flap. The slots are closed with shutters on the outer side of the wing.