WE CLAIM:
1. An aircraft (10) extending between a forward end (14) and an aft
end (16), the aircraft (10) comprising:
a fuselage (20) extending from the forward end (14) of the aircraft (10) towards the aft end (16) of the aircraft (10); and
an aft engine (200) mounted to the fuselage (20) proximate the aft end (16) of the aircraft (10), the aft engine (200) defining a central axis (220) and comprising
a fan (222) rotatable about the central axis (220) and including a
plurality of fan blades (228); and
a nacelle (224) surrounding the plurality of fan blades (228) of the
fan (222) and defining an inlet (244), the inlet (244) defining a non-axis
symmetric shape with respect to the central axis (220) of the aft engine
(200).
2. The aircraft (10) as claimed in claim 1, wherein the aircraft (10) defines a mean line (18) extending from the forward end (14) to the aft end (16), and wherein the nacelle (224) extends substantially 360 degrees around the mean line (18) of the aircraft (10).
3. The aircraft (10) as claimed in claim 1, wherein the nacelle (224) defines the inlet (244) with the fuselage (20) of the aircraft (10).
4. The aircraft (10) as claimed in claim 3, wherein the inlet (244) defined by the nacelle (224) extends substantially 360 degrees around the fuselage (20) of the aircraft (10).
5. The aircraft (10) as claimed in claim 1, wherein the nacelle (224) extends substantially 360 degrees around the central axis (220) of the aft engine
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(200).
6. The aircraft (10) as claimed in claim 1, wherein the inlet (244) includes a top half positioned above the central axis (220) and a bottom half positioned below the central axis (220), wherein the top half of the inlet (244) defines a top half inlet area, wherein the bottom half of the inlet (244) defines a bottom half inlet area, and wherein the bottom half inlet area is greater than the top half inlet area.
7. The aircraft (10) as claimed in claim 1, wherein the inlet (244) defines a height having a midpoint (245), wherein the inlet (244) includes a top half positioned above the midpoint (245) of the height and a bottom half positioned below the midpoint (245) of the height, wherein the top half of the inlet (244) defines a top half inlet area, wherein the bottom half of the inlet (244) defines a bottom half inlet area, and wherein the bottom half inlet area is greater than the top half inlet area.
8. The aircraft (10) as claimed in claim 1, wherein the fuselage (20) defines a recessed portion, and wherein the nacelle (224) is configured to extend at least partially around the recessed portion of the fuselage (20).
9. The aircraft (10) as claimed in claim 1, wherein the nacelle (224) defines a highlight plane, and wherein the nacelle (224) defines a non-axis symmetric shape at the highlight plane.
10. An aft engine (200) defining a central axis (220) and configured to be mounted to an aircraft (10) at an aft end (16) of the aircraft (10), the aft engine (200) comprising:
a fan (222) rotatable about the central axis (220) and including a plurality of fan blades (228); and
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a nacelle (224) surrounding the plurality of fan blades (228) of the fan (222) and defining an inlet (244), the inlet (244) defining a non-axis symmetric shape with respect to the central axis (220) of the aft engine (200).
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