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A variable area fan nozzle assembly for a turbofan engine includes a nacelle having an aft edge and a translating nozzle segment having a forward edge and a first end. The nozzle segment is movably disposed behind the aft edge such that an upstream bypass flow exit is defined between the aft edge an

A variable area fan nozzle assembly for a turbofan engine includes a nacelle having an aft edge and a translating nozzle segment having a forward edge and a first end. The nozzle segment is movably disposed behind the aft edge such that an upstream bypass flow exit is defined between the aft edge and the forward edge when the nozzle segment is in a deployed position. A deflector is disposed between the aft edge and the forward edge proximate to the first end. The deflector substantially prevents bypass flow from exiting the upstream bypass flow exit in a region that is proximate to the first end.

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1. A nacelle assembly for a turbofan aircraft engine having a centerline, the nacelle comprising: (a) a forward nacelle portion having an outer fairing and a trailing edge;(b) a translatable variable area fan nozzle comprising at least one nozzle segment, the nozzle segment having a leading edge and

1. A nacelle assembly for a turbofan aircraft engine having a centerline, the nacelle comprising: (a) a forward nacelle portion having an outer fairing and a trailing edge;(b) a translatable variable area fan nozzle comprising at least one nozzle segment, the nozzle segment having a leading edge and a first end and being selectively movable between a stowed position and one or more deployed positions, wherein in the deployed positions, an upstream bypass flow exit is formed between the trailing edge and the leading edge and in at least the stowed position, the nozzle segment overlaps with the forward nacelle trailing edge;(c) a split beavertail fairing comprising an upstream fairing portion on the outer fairing of the forward nacelle portion and a downstream fairing portion on the first end of at least one nozzle segment, wherein when the nozzle segment is in the stowed position, the upstream fairing portion and the downstream fairing portion combine to form a substantially continuous outer surface extending between the forward nacelle portion and the at least one nozzle segment; and(d) a deflector located proximate to the first end of the at least one nozzle segment and adjacent the split beavertail fairing, wherein the deflector is configured to substantially block air flow that exits the nacelle assembly through the upstream bypass flow exit from contacting the split beavertail fairing when the nozzle segment is in the deployed position;wherein the deflector is affixed to the nacelle and rearwardly extends from the trailing edge;wherein at least a portion of the deflector overlaps a portion of the nozzle segment when the nozzle segment is in a fully deployed position of said one or more deployed positions. 2. A nacelle assembly according to claim 1 wherein the forward nacelle portion is a stationary forward cowl. 3. A nacelle assembly according to claim 1 wherein the forward nacelle portion is a translatable thrust reverser sleeve. 4. A nacelle assembly according to claim 1 wherein a gap is formed between the upstream fairing portion and the downstream fairing portion when the nozzle segment is in the one or more deployed positions, and wherein the deflector is configured to substantially block air flow that exits the nacelle assembly through the upstream bypass flow exit from passing through the gap when the nozzle segment is in the one or more deployed positions. 5. A variable area fan nozzle assembly for a turbofan engine assembly having a primary bypass flow exit for discharging engine bypass flow, the assembly comprising: (a) a forward nacelle portion having a trailing edge;(b) a translating nozzle segment having a leading edge and a first end;(c) support means for movably supporting the first end of the translating nozzle segment such that the nozzle segment is movable between a stowed position and a deployed position, wherein an upstream bypass flow exit is formed between the leading edge and the trailing edge when the nozzle segment is in the deployed position and in at least the stowed position, the nozzle segment overlaps with the forward nacelle trailing edge;(d) a fairing at least partially covering the support means; and(e) means for substantially preventing air from passing through the upstream bypass flow exit in a region proximate to the fairing;wherein the means for substantially preventing air from passing through the upstream bypass flow exit proximate to the fairing comprises a deflector adjacent to the fairing and attached to the forward nacelle portion and rearwardly extending from the trailing edge;wherein at least a portion of the deflector overlaps a portion of the nozzle segment when the nozzle segment is in the fully deployed position.