Aircraft nacelle equipped with at least one thrust reversal device comprising at least one longitudinal deflector, aircraft comprising at least one propulsion unit having such a nacelle

An aircraft nacelle comprising:

• an outer surface, extending between an upstream end and a downstream end, configured to channel an air stream flowing in a longitudinal direction from the upstream end to the downstream end, and
• at least one thrust reversal device which comprises:
• at least one lateral opening which is remote from the upstream end and the downstream end, passes through the aircraft nacelle and is delimited by an upper edge and a lower edge,
• at least one movable part configured to occupy a first position, corresponding to an inactivated state of the at least one thrust reversal device, in which the at least one movable part shuts off the at least one lateral opening, and a second position, corresponding to an activated state of the at least one thrust reversal device, in which the at least one movable part at least partially clears the at least one lateral opening,
• at least one deflection system configured to occupy a first position, when the at least one thrust reversal device is in the inactivated state, in which the at least one deflection system does not interfere with the air stream channeled in the aircraft nacelle, and a second position, when the at least one thrust reversal device is in the activated state, in which the at least one deflection system interferes with the air stream channeled in the aircraft nacelle and orients the at least one deflection system in radial directions toward the at least one lateral opening, and,
• at least one orientation system configured to orient the air stream deflected by the at least one deflection system, wherein the at least one orientation system comprises:
• at least one transverse deflector positioned approximately in a plane perpendicular to the longitudinal direction, having a first end connected to the upper edge of the at least one lateral opening and a second end connected to the lower edge of the at least one lateral opening and configured to orient the air stream deflected by the at least one deflection system in the radial directions and toward the upstream end of the aircraft nacelle,
• at least one longitudinal deflector positioned approximately in a plane parallel to the longitudinal direction and configured to orient the air stream deflected by the at least one deflection system in at least one direction that forms an angle with one of the radial directions, and
• a main longitudinal deflector which has a V-shaped cross section and extends between a first end and a second end of the main longitudinal deflector, the main longitudinal deflector being substantially symmetrical with respect to a longitudinal plane of symmetry;
• wherein the main longitudinal deflector comprises two wings which are substantially symmetrical with respect to the longitudinal plane of symmetry and each extend between an inner edge and an outer edge, the inner edge being contiguous and closer to the at least one deflection system than the outer edge.