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Engine nacelles for use with aircraft. In one embodiment, an engine nacelle includes an inlet having an inlet aperture and an outlet having an outlet aperture. In one aspect of this embodiment, the engine nacelle further includes a first side portion, a second side portion, and a third side portion.

Engine nacelles for use with aircraft. In one embodiment, an engine nacelle includes an inlet having an inlet aperture and an outlet having an outlet aperture. In one aspect of this embodiment, the engine nacelle further includes a first side portion, a second side portion, and a third side portion. The first side portion can extend at least generally between a first edge portion of the inlet aperture and a third edge portion of the outlet aperture. The second side portion can be offset from the first side portion and extend at least generally between a second edge portion of the inlet aperture and a fourth edge portion of the outlet aperture to define a first interior portion. The third side portion can be offset from the second side portion and extend at least generally from the second edge portion of the inlet aperture toward the fourth edge portion of the outlet aperture to define a second interior portion. In another aspect of this embodiment, the first interior portion is configured to house an engine, and the second interior portion is configured to house a landing gear assembly.

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1. An engine nacelle for use with an aircraft, the engine nacelle comprising:an air inlet configured to direct incoming air from an inlet aperture to an aircraft engine; a gear bay at least approximately laterally offset from the air inlet, wherein the gear bay is configured to house a landing gear

1. An engine nacelle for use with an aircraft, the engine nacelle comprising:an air inlet configured to direct incoming air from an inlet aperture to an aircraft engine; a gear bay at least approximately laterally offset from the air inlet, wherein the gear bay is configured to house a landing gear assembly having a wheel truck, wherein the wheel truck is moveable between a stowed position within the gear bay and a deployed position offset from the gear bay, and wherein the wheel truck is configured to support at least a portion of the weight of the aircraft when the wheel truck is in the deployed position; and a landing gear trunnion fixedly attached at least proximate to the gear bay and configured to be positioned below a wing of the aircraft, and wherein the landing gear assembly is pivotally moveable about the landing gear trunnion to position the wheel truck in the deployed position. 2. The engine nacelle of claim 1, wherein the landing gear assembly is pivotally moveable about the landing gear trunnion parallel to a longitudinal axis of the aircraft to position the wheel truck in the deployed position.3. An engine nacelle for use with an aircraft, the engine nacelle comprising:an air inlet configured to direct incoming air from an inlet aperture to an aircraft engine, wherein the inlet aperture is configured to face at least generally away from a wing root portion of the aircraft; a gear bay at least approximately laterally offset from the air inlet; and a landing gear assembly configured to be positioned in the gear bay in vertical alignment with a fuel tank, the fuel tank being positioned in a wing of the aircraft, the landing gear assembly having a wheel truck, that is moveable between a stowed position within the gear bay and a deployed position offset from the gear bay, and wherein the wheel truck is configured to support at least a portion of the weight of the aircraft when the wheel truck is in the deployed position. 4. The engine nacelle of claim 3 wherein the gear bay is configured to be positioned between the air inlet and a fuselage of the aircraft.5. The engine nacelle of claim 3, further comprising the wheel truck, wherein the wheel truck is positioned at least generally aft of the inlet aperture when the wheel truck is in the deployed position.6. An engine nacelle for use with an aircraft, the engine nacelle comprising:an air inlet configured to direct incoming air from an inlet aperture to an aircraft engine; a gear bay at least approximately laterally offset from the air inlet; a landing gear assembly configured to be positioned in the gear bay in vertical alignment with a fuel tank, the fuel tank being positioned in a wing of the aircraft, the landing gear assembly having a wheel truck, that is moveable between a stowed position within the gear bay and a deployed position offset from the gear bay, and wherein the wheel truck is configured to support at least a portion of the weight of the aircraft when the wheel truck is in the deployed position; and at least one landing gear door proximate to the gear bay, the landing gear door having a closed position and an open position, wherein the landing gear door is at least proximate to the wheel truck when the landing gear door is in the open position and the wheel truck is in the deployed position. 7. The engine nacelle of claim 6 wherein the aircraft engine is a jet engine, and wherein the engine nacelle further comprises the jet engine.8. An engine nacelle for use with an aircraft, the engine nacelle comprising:an inlet having an inlet aperture, the inlet aperture including a first edge portion and a second edge portion offset from the first edge portion; an outlet having an outlet aperture, the outlet aperture including a third edge portion and a fourth edge portion offset from the third edge portion; a first side portion extending at least generally between the first edge portion of the inlet aperture and the third edge portion of the outlet aperture; a second side portion offset from the first side portion toward a fuselage of the aircraft, the second side portion extending at least generally between the second edge portion of the inlet aperture and the fourth edge portion of the outlet aperture; an engine positioned within the first and second side portions, wherein the inlet aperture is configured to direct air to the engine and the outlet aperture is configured to direct exhaust gas from the engine; and a landing gear assembly positioned within the first and second side portions, wherein the landing gear assembly includes a wheel truck moveable between a stowed position within the nacelle and a deployed position offset from the nacelle, wherein the wheel truck is configured to support at least a portion of the weight of the aircraft when the wheel truck is in the deployed position, and wherein the landing gear assembly is configured to be positioned in vertical alignment with a fuel tank, the fuel tank being positioned in a wing of the aircraft. 9. The engine nacelle of claim 8, further comprising a third side portion positioned at least approximately between the engine and the landing gear assembly.10. The engine nacelle of claim 8, further comprising a third side portion positioned at least approximately between the first and second side portions, the third side portion extending at least generally from the second edge portion of the inlet aperture toward the fourth edge portion of the outlet aperture to at least partially define a first interior portion between the first and third side portions and a second interior portion between the second and third side portions, wherein the engine is housed in the first interior portion and the landing gear assembly is housed in the second interior portion.11. The engine nacelle of claim 8 wherein the landing gear assembly is at least approximately laterally offset from the engine.12. The engine nacelle of claim 8 wherein the engine is a jet engine.13. The engine nacelle of claim 8 wherein the inlet aperture is at least approximately rectangular in shape.14. The engine nacelle of claim 8 wherein the first side portion is at least approximately cambered and the second side portion is at least approximately flat.15. The engine nacelle of claim 8 wherein the wheel truck is positioned at least generally aft of the inlet aperture when the wheel truck is in the deployed position.16. The engine nacelle of claim 8 wherein the wheel truck is positioned at least generally aft of the inlet aperture and at least generally forward of the engine when the wheel truck is in the deployed position.17. An engine nacelle for use with an aircraft, the engine nacelle comprising:an inlet having an inlet aperture, the inlet aperture including a first edge portion and a second edge portion offset from the first edge portion; an outlet having an outlet aperture, the outlet aperture including a third edge portion and a fourth edge portion offset from the third edge portion; a first side portion extending at least generally between the first edge portion of the inlet aperture and the third edge portion of the outlet aperture; a second side portion offset from the first side portion toward a fuselage of the aircraft, the second side portion extending at least generally between the second edge portion of the inlet aperture and the fourth edge portion of the outlet aperture; an engine positioned within the first and second side portions, wherein the inlet aperture is configured to direct air to the engine and the outlet aperture is configured to direct exhaust gas from the engine; a landing gear assembly positioned within the first and second side portions, wherein the landing gear assembly includes a wheel truck moveable between a stowed position within the nacelle and a deployed position offset from the nacelle, and wherein the wheel truck is configured to support at least a portion of the weight of the aircraft when the wheel truck is in the deployed position; and a landing gear trunnion configured to be positioned below a wing of the aircraft, wherein the landing gear assembly is pivotally connected to the landing gear trunnion and pivotally moveable about the landing gear trunnion to position the wheel truck in the deployed static position. 18. An aircraft comprising:a fuselage; a wing having a wing root portion fixedly attached to the fuselage, a wing tip portion offset from the wing root portion, and a wing lower surface extending at least generally between the wing tip portion and the wing root portion; a fuel tank positioned in the wing; ;and an engine nacelle positioned at least proximate to the wing lower surface, the engine nacelle including: an air inlet configured to direct incoming air from an inlet aperture to an aircraft engine; a gear bay at least approximately laterally offset from the air inlet; and a landing gear assembly positioned in the gear bay in vertical alignment with the fuel tank, the landing gear assembly having a wheel truck, that is moveable between a stowed position within the gear bay and a deployed position offset from the gear bay, and wherein the wheel truck is configured to support at least a portion of the weight of the aircraft when the wheel truck is in the deployed position. 19. An aircraft comprising:a fuselage; a wing having a wing root portion fixedly attached to the fuselage, a wing tip portion offset from the wing root portion, and a wing lower surface extending at least generally between the wing tip portion and the wing root portion; an engine nacelle positioned at least proximate to the wing lower surface, the engine nacelle including: an air inlet configured to direct incoming air from an inlet aperture to an aircraft engine; and a gear bay at least approximately laterally offset from the air inlet, wherein the gear bay is configured to house a landing gear assembly having a wheel truck, wherein the wheel truck is moveable between a stowed position within the gear bay and a deployed position offset from the gear bay, and wherein the wheel truck is configured to support at least a portion of the weight of the aircraft when the wheel truck is in the deployed position; and a fuel tank portion configured to carry fuel, wherein the fuel tank portion is positioned in vertical alignment with the landing gear assembly. 20. The aircraft of claim 19, wherein the fuselage includes a passenger cabin configured to carry passengers.21. The aircraft of claim 19, further comprising a center of gravity positioned at least proximate to the fuselage, wherein the aircraft engine is positioned aft of the center of gravity, wherein the deployed position of the wheel truck is positioned aft of the center of gravity and forward of the aircraft engine, and wherein the inlet aperture is positioned forward of the deployed position of the wheel truck.22. The aircraft of claim 19, further comprising a center of gravity positioned at least proximate to the fuselage, wherein the fuel tank portion is positioned aft of the center of gravity.23. A method for manufacturing an aircraft, the method comprising:joining a wing to a fuselage; positioning an engine nacelle at least approximately below the wing; positioning an engine at least approximately in the engine nacelle; positioning a gear bay at least approximately in the engine nacelle at least approximately laterally offset from the engine, wherein the gear bay is configured to house a landing gear assembly having a wheel truck moveable between a stowed position within the nacelle and a deployed position offset from the nacelle, wherein the landing gear assembly is configured to support at least a portion of the weight of the aircraft when the wheel truck is in the deployed position; and installing a fuel tank portion in the wing, the fuel tank portion configured to carry fuel in vertical alignment with the landing gear assembly. 24. The method of claim 23 wherein positioning a gear bay at least approximately in the nacelle includes positioning a gear bay between the fuselage.25. The method of claim 23 wherein the fuselage has a longitudinal axis, and wherein the method further comprises fixedly attaching a landing gear trunnion at least proximate to the gear bay, wherein the landing gear assembly is pivotally connected to the landing gear trunnion and pivotally moveable about the trunnion parallel to the longitudinal axis to position the wheel truck in the deployed position.