Aircraft with an offset nacelle aligned with the wake of the wing
An aircraft includes a fuselage carrying a nacelle of the aircraft offset relative to a wing of the aircraft. The nacelle forms an air inlet fairing of a propulsion assembly. The nacelle includes a lower wall and an upper wall delimiting together a height of the nacelle. The lower wall includes an air inlet edge being contiguous with a trailing edge of the wing.
1. An aircraft comprising;
a nacelle; and
a fuselage carrying the nacelle that is offset relative to a wing of the aircraft,
wherein the nacelle forms an air inlet fairing of a propulsion assembly, and includes a lower wall and an upper wall delimiting together a height of the nacelle, the lower wall comprising an air inlet edge being contiguous with a trailing edge of the wing such that the air inlet edge of the lower wall of the nacelle is aligned with a wake of the wing by providing a space for a flow of a boundary layer of the wing between the trailing edge of the wing and the air inlet edge of the lower wall of the nacelle.
2. The aircraft according to claim 1 , wherein the nacelle extends laterally from the fuselage of the aircraft in an oblong rectangular shape.
3. The aircraft according to claim 1 , wherein the air inlet edge of the lower wall is downstream of an upper surface of the wing while being parallel to the trailing edge of the wing.
4. The aircraft according to claim 1 , wherein the propulsion assembly is formed of mechanical transmission turbines powered by a mechanical transmission generator, each mechanical transmission turbine being associated with a fan.
5. The aircraft according to claim 1 , wherein the propulsion assembly comprises a plurality of fans.
6. The aircraft according to claim 5 , wherein the nacelle comprises partitions of the fans.
7. The aircraft according to claim 1 , wherein the nacelle is mechanically connected to the wing by at least one pylon.
8. The aircraft according to claim 7 , wherein the propulsion assembly is formed of gas turbines powered by a gas generator, each gas turbine being associated with a fan.
9. The aircraft according to claim 8 , wherein the at least one pylon is configured to allow the passage of a gas supply conduit of the gas turbines.
10. The aircraft according to claim 8 , wherein the gas generator is integrated into the nacelle.
11. The aircraft according to claim 8 , wherein the gas generator is directly coupled to one of the fans of the propulsion assembly.
12. The aircraft according to claim 8 , wherein the gas generator is carried by the lower surface of the wing.
13. The aircraft according to claim 8 , wherein the gas generator is carried directly by the fuselage of the aircraft.
14. The aircraft according to claim 8 , wherein outlet nozzles of the gas turbines have a Y shape for the passage of gas supply conduits of each of the gas turbines.
15. The aircraft according to claim 14 , further comprising a distribution duct configured to envelop each of the gas supply conduits extending along the nacelle.