초록 ▼

An aircraft including: a fuselage and two wings to which engine nacelles are attached and that are each connected laterally to the fuselage, one on each side thereof, by a central fairing. The central fairing includes, facing each wing, two opposed surfaces connected one to a suction face side and t

An aircraft including: a fuselage and two wings to which engine nacelles are attached and that are each connected laterally to the fuselage, one on each side thereof, by a central fairing. The central fairing includes, facing each wing, two opposed surfaces connected one to a suction face side and the other to a pressure face side of the wing and that extend longitudinally along the fuselage. At least one of the two surfaces includes at least one local geometric deformation configured to generate lateral aerodynamic disturbances on the central fairing toward the wing to control the flow of air over the wing.

대표청구항 ▼

1. An aircraft comprising: a fuselage; andtwo wings, to which are fixed engine nacelles, each wing being joined laterally to the fuselage on opposite sides thereof by a unitary central fairing, the central fairing including, on each wing, a first surface and a second surface opposite the first surfa

1. An aircraft comprising: a fuselage; andtwo wings, to which are fixed engine nacelles, each wing being joined laterally to the fuselage on opposite sides thereof by a unitary central fairing, the central fairing including, on each wing, a first surface and a second surface opposite the first surface, the first and second surfaces being joined to upper and lower surfaces of the wing, respectively, and extending longitudinally along the fuselage,wherein at least one of the first and second surfaces includes at least one local geometric deformation configured to generate in a controlled manner lateral aerodynamic perturbations from the central fairing toward the wing to control airflow over the wing. 2. An aircraft according to claim 1, wherein the at least one local geometric deformation comprises a primary curvature that extends along the fuselage in a longitudinal direction and a secondary curvature that extends along a height of the fuselage in a direction transverse to the longitudinal direction. 3. An aircraft according to claim 1, wherein the at least one local geometric deformation is defined by a reduction of the local radius of curvature of at least one surface zone. 4. An aircraft according to claim 1, wherein a location and an amplitude of the at least one local geometric deformation depend on aerodynamic parameters of the aircraft. 5. An aircraft according to claim 4, wherein the aerodynamic parameters relate to the fuselage, the wings, the engine nacelles, and a speed of the aircraft. 6. An aircraft according to claim 1, wherein the local geometric deformation is shaped as a local convexity. 7. An aircraft according to claim 6, wherein the convexity is shaped as a hump. 8. An aircraft according to claim 1, wherein the local geometric deformation is shaped as a local concavity. 9. An aircraft according to claim 8, wherein the concavity is shaped as a hollow. 10. An aircraft according to claim 9, wherein the hollow is defined by two inclined surface portions that intersect at a bottom of the hollow in a zone of slope discontinuity. 11. An aircraft according to claim 1, wherein at least one of the first and second surfaces includes a plurality of successive local geometric deformations extending along the fuselage and alternating locally between convexity and concavity. 12. An aircraft according to claim 1, wherein the at least one local geometric deformation is on the first surface joined to the upper surface of the wing. 13. An aircraft according to claim 1, wherein the at least one local geometric deformation is on the second surface joined to the lower surface of the wing. 14. An aircraft according to claim 1, wherein the central fairing includes an assemblage of a plurality of panels, each of the panels having a surface portion, and wherein each of the first and second surfaces of the central fairing on each wing is formed by a group of surface portions of the plurality of panels arranged next to one another. 15. The aircraft according to claim 1, wherein the first and second surfaces extend longitudinally along the fuselage such that a portion of the wing immediately adjacent to the fuselage is entirely surrounded by the first and second surfaces. 16. The aircraft according to claim 1, wherein the at least one local geometric deformation is behind a leading edge of the wing. 17. The aircraft according to claim 1, wherein the generated lateral aerodynamic perturbations include pressure waves that propagate in a direction of a free tip of the wing. 18. An aircraft comprising: a fuselage;two wings connected to the fuselage on opposite sides thereof; anda central fairing that joins each wing laterally to the fuselage, the central fairing including a first surface and a second surface, the first and second surfaces being joined to upper and lower surfaces of the wing, respectively, and extending longitudinally along the fuselage,wherein at least one of the first and second surfaces is configured to be mechanically deformed in flight so as to include at least one local geometric deformation that generates lateral aerodynamic perturbations from the central fairing toward the wing to control airflow over the wing. 19. An aircraft comprising: a fuselage; andtwo wings, to which are fixed engine nacelles, each wing being joined laterally to the fuselage on opposite sides thereof by a central fairing, the central fairing including, on each wing, a first surface and a second surface opposite the first surface, the first and second surfaces being joined to upper and lower surfaces of the wing, respectively, and extending longitudinally along the fuselage,wherein at least one of the first and second surfaces includes at least one local geometric deformation configured to generate lateral aerodynamic perturbations from the central fairing toward the wing to control airflow over the wing, andwherein at least one of the first and second surfaces includes a plurality of successive local geometric deformations extending along the fuselage and alternating locally between convexity and concavity. 20. An aircraft comprising: a fuselage; andtwo wings, to which are fixed engine nacelles, each wing being joined laterally to the fuselage on opposite sides thereof by a unitary central fairing, the central fairing including, on each wing, a first surface and a second surface opposite the first surface, the first and second surfaces being joined to upper and lower surfaces of the wing, respectively, and extending longitudinally along the fuselage,wherein at least one of the first and second surfaces includes at least one local geometric deformation configured to generate lateral aerodynamic perturbations from the central fairing toward the wing to control airflow over the wing, andwherein the at least one local geometric deformation is shaped as a local convexity disposed behind a leading edge of the wing.