대표
청구항
▼
We claim: 1. An aircraft comprising: a fuselage configured to carry a payload and having a longitudinal axis, the fuselage having a forward portion and an aft portion, the aft portion defining a generally constant-width planform; a wing extending from the fuselage adjacent to the aft portion of the fuselage, wherein the wing has an upper surface, a lower surface, a forward region with a leading edge, and an aft region with a trailing edge; a passenger cabin positioned within the aft portion of the fuselage, the passenger cabin having first, second, thir...
We claim: 1. An aircraft comprising: a fuselage configured to carry a payload and having a longitudinal axis, the fuselage having a forward portion and an aft portion, the aft portion defining a generally constant-width planform; a wing extending from the fuselage adjacent to the aft portion of the fuselage, wherein the wing has an upper surface, a lower surface, a forward region with a leading edge, and an aft region with a trailing edge; a passenger cabin positioned within the aft portion of the fuselage, the passenger cabin having first, second, third, and fourth passenger seat sections, with each of the first, second, third, and fourth seat sections having at least two passenger seats abreast and with neighboring passenger seat sections being spaced apart from each other to form first, second, and third passenger aisles positioned at least generally parallel to the longitudinal axis of the fuselage; and a propulsion system at least proximate to the aft region of the wing, with at least part of the propulsion system positioned between the upper and lower surfaces of the wing, the propulsion system having at least one inlet aperture positioned beneath the wing lower surface or above the wing upper surface, at least one engine positioned aft of and vertically offset from the at least one inlet aperture, and at least one exhaust nozzle aft of the at least one engine. 2. The aircraft of claim 1 wherein each of the first, second, third, and fourth seat sections includes at least 54 passenger seats. 3. An aircraft comprising: a fuselage configured to carry a payload and having a longitudinal axis, the fuselage having a forward portion and an aft portion, the aft portion defining a generally constant-width planform; a wing extending from the fuselage adjacent to the aft portion of the fuselage; and a passenger cabin positioned within the aft portion of the fuselage, the passenger cabin having first, second, third, and fourth passenger seat sections, with each of the first, second, third, and fourth seat sections having at least two passenger seats abreast and with neighboring passenger seat sections being spaced apart from each other to form first, second, and third passenger aisles positioned at least generally parallel to the longitudinal axis of the fuselage, wherein each of the first, second, third, and fourth passenger seat sections includes a portion having three seats abreast and extending for at least 14 contiguous rows. 4. An aircraft comprising: a fuselage configured to carry a payload and having a longitudinal axis, the fuselage having a forward portion and an aft portion, the aft portion defining a generally constant-width planform; a wing extending from the fuselage adjacent to the aft portion of the fuselage, wherein the wing has an upper surface, a lower surface, a forward region with a leading edge, and an aft region with a trailing edge; a passenger cabin positioned within the aft portion of the fuselage, the passenger cabin having first, second, third, and fourth passenger seat sections, with each of the first, second, third, and fourth seat sections having at least two passenger seats abreast and with neighboring passenger seat sections being spaced apart from each other to form first, second, and third passenger aisles positioned at least generally parallel to the longitudinal axis of the fuselage; and a propulsion system at least proximate to the aft region of the wing, with at least part of the propulsion system positioned between the upper and lower surfaces of the wing, the propulsion system having at least one inlet aperture, positioned beneath the wing lower surface or above the wing upper surface, at least one engine positioned aft of and vertically offset from the at least one inlet aperture, and at least one exhaust nozzle aft of the at least one engine, wherein the wing and the propulsion system are configured to operate at a cruise Mach number ranging from about 0.80 to about 0.98. 5. The aircraft of claim 4 wherein the wing and the propulsion system are configured to operate at a cruise Mach number ranging from about 0.90 to about 0.96. 6. The aircraft of claim 1 wherein the fuselage is configured to carry a commercial passenger payload of at least 230 passengers and/or a commercial cargo payload. 7. The aircraft of claim 1 wherein the wing has a delta planform. 8. The aircraft of claim 1 wherein the wing has a forward region with a leading edge, the leading edge having a first part proximate to the fuselage with a first sweep angle and a second part outboard of the first part with a second sweep angle less than the first sweep angle. 9. The aircraft of claim 1 further comprising: a cargo hold positioned within the aft portion of the fuselage; and a center of gravity through which the resultant of the gravitational forces on all components of the aircraft acts, the center of gravity having a position within the cargo hold. 10. The aircraft of claim 1 further comprising: a cargo hold positioned within the aft portion of the fuselage; a fuel volume positioned within the wing and configured to carry fuel; and a center of gravity through which the resultant of the gravitational forces on all components of the aircraft acts, the center of gravity having a first position when the fuel volume is approximately full of fuel and a second position when the fuel volume is approximately empty of fuel, the first and second positions being located within the cargo hold. 11. The aircraft of claim 1 wherein the aft portion of the fuselage further includes an upper fuselage surface spaced apart from a lower fuselage surface, wherein the wing extends from the fuselage between the upper and lower fuselage surfaces adjacent to the aft portion of the fuselage, and wherein the aircraft further comprises: at least a first window positioned in the upper fuselage surface directly adjacent the first passenger seat section; and at least a second window positioned in the upper fuselage surface directly adjacent the fourth passenger seat section. 12. The aircraft of claim 1 wherein the fuselage includes first windows adjacent the first passenger seat section and second windows adjacent the fourth passenger seat section, and wherein each of the seats in the first, second, third, and fourth passenger seat sections has visual access to at least one of the first windows and at least one of the second windows. 13. The aircraft of claim 3 wherein the aft portion of the fuselage includes an upper interior surface spaced apart from a lower interior surface, wherein the passenger cabin is absent any load-bearing member extending vertically between the lower interior surface and the upper interior surface between the seat sections. 14. The aircraft of claim 1 wherein the aft portion of the fuselage includes an upper fuselage surface spaced apart from a lower fuselage surface, wherein the aft portion of the fuselage further includes a cargo hold and a cargo door configured to facilitate loading of cargo into the cargo hold, the cargo door being operably integrated with the lower surface of the aft portion of the fuselage along the longitudinal axis of the fuselage. 15. The aircraft of claim 1 further comprising a generally horizontal and moveable elevator surface adjacent to the aft portion of the fuselage. 16. An aircraft comprising: a fuselage configured to carry a payload and having a longitudinal axis, the fuselage having a forward portion and an aft portion, the aft portion defining a generally constant-width planform; a wing extending from the fuselage adjacent to the aft portion of the fuselage, wherein the wing has an upper surface, a lower surface, a forward region with a leading edge, and an aft region with a trailing edge; a passenger cabin positioned within the aft portion of the fuselage, the passenger cabin having first, second, third, and fourth passenger seat sections, with each of the first, second, third, and fourth seat sections having at least two passenger seats abreast and with neighboring passenger seat sections being spaced apart from each other to form first, second, and third passenger aisles positioned at least generally parallel to the longitudinal axis of the fuselage; a propulsion system at least proximate to the aft region of the wing, with at least part of the propulsion system positioned between the upper and lower surfaces of the wing, the propulsion system having at least one inlet aperture positioned beneath the wing lower surface or above the wing upper surface, at least one engine positioned aft of and vertically offset from the at least one inlet aperture, and at least one exhaust nozzle aft of the at least one engine; a generally horizontal and moveable first control surface integrated with the fuselage adjacent to the aft portion of the fuselage; and a generally horizontal and moveable second control surface integrated with the aft region of the wing outboard of the at least one engine. 17. The aircraft of claim 3 wherein the aft portion of the fuselage has a generally oval cross-sectional shape and the passenger cabin has a width of between about 25 feet and about 35 feet. 18. The aircraft of claim 3 wherein the wing has a leading edge and a trailing edge, and wherein the aircraft further comprises a moveable elevon surface at the wing trailing edge. 19. The aircraft of claim 1 wherein the fuselage is configured for a military payload. 20. An aircraft comprising: a fuselage configured to carry a payload and having a longitudinal axis, the fuselage having a forward portion and an aft portion, the aft portion defining a generally constant-width planform; a wing extending from the fuselage adjacent to the aft portion of the fuselage, wherein the wing has an upper surface, a lower surface, a forward region with a leading edge, and an aft region with a trailing edge; a passenger cabin positioned within the aft portion of the fuselage, the passenger cabin having first, second, third, and fourth passenger seat sections, with each of the first, second, third, and fourth seat sections having at least two passenger seats abreast and with neighboring passenger seat sections being spaced apart from each other to form first, second, and third passenger aisles positioned at least generally parallel to the longitudinal axis of the fuselage, wherein the fuselage includes first windows adjacent the first passenger seat section and second windows adjacent the fourth passenger seat section, and wherein each of the seats in the first, second, third, and fourth passenger seat sections provides visual access to at least one of the first windows and at least one of the second windows; and a propulsion system at least proximate to the aft region of the wing, with at least part of the propulsion system positioned between the upper and lower surfaces of the wing, the propulsion system having at least one inlet aperture positioned beneath the wing lower surface or above the wing upper surface, at least one engine positioned aft of and vertically offset from the at least one inlet aperture, and at least one exhaust nozzle aft of the at least one engine. 21. An aircraft comprising: a fuselage configured to carry a payload and having a longitudinal axis, the fuselage having a forward portion and an aft portion, the aft portion defining a generally constant-width planform; a wing extending from the fuselage adjacent to the aft portion of the fuselage; a passenger cabin positioned within the aft portion of the fuselage, the passenger cabin having first, second, third, and fourth passenger seat sections, with each of the first, second, third, and fourth seat sections having at least two passenger seats abreast and with neighboring passenger seat sections being spaced apart from each other to form first, second, and third passenger aisles positioned at least generally parallel to the longitudinal axis of the fuselage, wherein the fuselage includes first windows adjacent the first passenger seat section and second windows adjacent the fourth passenger seat section, and wherein each of the seats in the first, second, third, and fourth passenger seat sections provides visual access to at least one of the first windows and at least one of the second windows; a cargo hold positioned within the aft portion of the fuselage; and a center of gravity through which the resultant of the gravitational forces on all components of the aircraft acts, the center of gravity positioned within the cargo hold. 22. The aircraft of claim 21 wherein the aft portion of the fuselage has an upper interior surface and a lower interior surface and a floor portion extending horizontally between the upper interior surface and the lower interior surface to separate the passenger cabin from the cargo hold, and wherein the passenger cabin is absent any load-bearing member extending vertically between the floor portion and the upper interior surface parallel to the longitudinal axis of the fuselage between the seat sections. 23. The aircraft of claim 21 wherein the aft portion of the fuselage has an upper interior surface and a lower interior surface and a floor portion extending horizontally between the upper interior surface and the lower interior surface to separate the passenger cabin from the cargo hold, and wherein the passenger cabin is absent any load-bearing member extending vertically between the floor portion and the upper interior surface between the seat sections. 24. The aircraft of claim 21 wherein the aft portion of the fuselage has an upper interior surface and a lower interior surface and a floor portion extending horizontally between the upper interior surface and the lower interior surface to separate the passenger cabin from the cargo hold, and wherein the passenger cabin is absent any member extending vertically between the floor portion and the upper interior surface between the seat sections. 25. The aircraft of claim 21 wherein each of the first, second, third, and fourth seat sections includes at least 54 passenger seats. 26. The aircraft of claim 21 wherein each of the first, second, third, and fourth passenger seat sections includes a portion having three seats abreast and extending for at least 14 contiguous rows. 27. The aircraft of claim 21 wherein the wing has an upper surface, a lower surface, a forward region with a leading edge, and an aft region with a trailing edge, wherein the aircraft further comprises a propulsion system at least proximate to the aft region of the wing, with at least part of the propulsion system positioned between the upper and lower surfaces of the wing, the propulsion system having at least one inlet aperture positioned beneath the wing lower surface or above the wing upper surface, at least one engine positioned aft of and vertically offset from the at least one inlet aperture, and at least one exhaust nozzle aft of the at least one engine, wherein the wing and the propulsion system are configured to operate at a cruise Mach number ranging from about 0.90 to about 0.96. 28. The aircraft of claim 21 wherein the aft portion of the fuselage further includes an upper fuselage surface spaced apart from a lower fuselage surface, wherein the wing extends from the fuselage between the upper and lower fuselage surfaces adjacent to the aft portion of the fuselage, and wherein the aircraft further comprises: at least a first window positioned in the upper fuselage surface directly adjacent the first passenger seat section; and at least a second window positioned in the upper fuselage surface directly adjacent the fourth passenger seat section. 29. The aircraft of claim 21 wherein the aft portion of the fuselage has a generally oval cross-sectional shape and the passenger cabin has a width of between about 25 feet and about 35 feet. 30. An aircraft comprising: a fuselage configured to carry a payload and having a longitudinal axis, the fuselage having a forward portion and an aft portion, the aft portion defining a generally constant-width planform; a wing extending from the fuselage adjacent to the aft portion of the fuselage, the wing having a forward region with a leading edge and an aft region with a trailing edge, the wing further having an upper surface and a lower surface; a propulsion system at least proximate to the aft region of the wing, with at least part of the propulsion system positioned between the upper and lower surfaces of the wing, the propulsion system having at least one inlet aperture positioned beneath the wing lower surface or above the wing upper surface, at least one engine positioned aft of and vertically offset from the at least one inlet aperture, and at least one exhaust nozzle aft of the at least one engine; and a passenger cabin positioned within the aft portion of the fuselage, the passenger cabin having first, second, third, and fourth passenger seat sections, with each of the first, second, third, and fourth seat sections having at least two passenger seats abreast and with neighboring passenger seat sections being spaced apart from each other to form first, second, and third passenger aisles positioned at least generally parallel to the longitudinal axis of the fuselage. 31. The aircraft of claim 30 wherein each of the first, second, third, and fourth seat sections includes at least 54 passenger seats. 32. The aircraft of claim 30 wherein each of the first, second, third, and fourth passenger seat sections includes a portion having three seats abreast and extending for at least 14 contiguous rows. 33. The aircraft of claim 30 wherein the wing includes a fuel volume configured to carry fuel for the propulsion system, and wherein the engine includes rotating components, further wherein the rotating components of the engine are positioned aft of the fuel volume. 34. The aircraft of claim 30 wherein the wing includes a fuel volume configured to carry fuel for the propulsion system, and wherein the engine includes rotating components, further wherein the rotating components of the engine are positioned aft of the fuel volume and the passenger cabin. 35. The aircraft of claim 30 wherein the wing and the propulsion system are configured to operate at a cruise Mach number ranging from about 0.90 to about 0.96. 36. The aircraft of claim 30 wherein the leading edge of the wing has a first part proximate to the fuselage with a first sweep angle and a second part outboard of the first part with a second sweep angle less than the first sweep angle. 37. The aircraft of claim 30 wherein the trailing edge of the wing is forward swept. 38. The aircraft of claim 30 further comprising: a cargo hold positioned within the aft portion of the fuselage; a fuel volume positioned within the wing and configured to carry fuel; and a center of gravity through which the resultant of the gravitational forces on all components of the aircraft acts, the center of gravity having a first position when the fuel volume is approximately full of fuel and a second position when the fuel volume is approximately empty of fuel, the first and second positions being located within the cargo hold. 39. The aircraft of claim 30 wherein the aft portion of the fuselage further includes an upper fuselage surface spaced apart from a lower fuselage surface, wherein the wing extends from the fuselage between the upper and lower fuselage surfaces adjacent to the aft portion of the fuselage, and wherein the aircraft further comprises: at least a first window positioned in the upper fuselage surface directly adjacent the first passenger seat section; and at least a second window positioned in the upper fuselage surface directly adjacent the fourth passenger seat section. 40. The aircraft of claim 30 further comprising a moveable elevator surface adjacent to the aft portion of the fuselage. 41. The aircraft of claim 30 further comprising a moveable elevon surface at the wing trailing edge. 42. The aircraft of claim 30 further comprising: a moveable first control surface integrated with the fuselage adjacent to the aft portion of the fuselage; and a moveable second control surface integrated with the aft region of the wing outboard of the at least one engine. 43. An aircraft comprising: a fuselage configured to carry a payload and having a longitudinal axis, a nose end, a tail end, a forward portion, and an aft portion, the forward portion extending forward directly from the aft portion and defining a generally continuously monotonically tapering planform between the aft portion and the nose end, the aft portion extending aft directly from the forward portion and defining a generally constant-width planform between the forward portion and the tail end; a wing extending from the fuselage adjacent to the aft portion of the fuselage, wherein the wing has an upper surface, a lower surface, a forward region with a leading edge, and an aft region with a trailing edge; a passenger cabin positioned within the aft portion of the fuselage, the passenger cabin having first, second, third, and fourth passenger seat sections, with each of the first, second, third, and fourth seat sections having at least two passenger seats abreast and with neighboring passenger seat sections being spaced apart from each other to form first, second, and third passenger aisles positioned at least generally parallel to the longitudinal axis of the fuselage; and a propulsion system at least proximate to the aft region of the wing, with at least part of the propulsion system positioned between the upper and lower surfaces of the wing, the propulsion system having at least one inlet aperture positioned beneath the wing lower surface or above the wing upper surface, at least one engine positioned aft of and vertically offset from the at least one inlet aperture, and at least one exhaust nozzle aft of the at least one engine. 44. The aircraft of claim 43 wherein the wing includes a fuel volume configured to carry fuel for the propulsion system, and wherein the engine includes rotating components, further wherein the rotating components of the engine are positioned aft of the fuel volume and the passenger cabin. 45. The aircraft of claim 43 wherein each of the first, second, third, and fourth seat sections includes at least 54 passenger seats. 46. An aircraft comprising: a fuselage configured to carry a payload and having a longitudinal axis, a nose end, a tail end, a forward portion, and an aft portion, the forward portion extending forward directly from the aft portion and defining a generally continuously monotonically tapering planform between the aft portion and the nose end, the aft portion extending aft directly from the forward portion and defining a generally constant-width planform between the forward portion and the tail end; a wing extending from the fuselage adjacent to the aft portion of the fuselage; and a passenger cabin positioned within the aft portion of the fuselage, the passenger cabin having first, second, third, and fourth passenger seat sections, with each of the first, second, third, and fourth seat sections having at least two passenger seats abreast and with neighboring passenger seat sections being spaced apart from each other to form first, second, and third passenger aisles positioned at least generally parallel to the longitudinal axis of the fuselage, wherein each of the first, second, third, and fourth passenger seat sections includes a portion having three seats abreast and extending for at least 14 contiguous rows. 47. An aircraft comprising: a fuselage configured to carry a payload and having a longitudinal axis, a nose end, a tail end, a forward portion, and an aft portion, the forward portion extending forward directly from the aft portion and defining a generally continuously monotonically tapering planform between the aft portion and the nose end, the aft portion extending aft directly from the forward portion and defining a generally constant-width planform between the forward portion and the tail end; a wing extending from the fuselage adjacent to the aft portion of the fuselage, wherein the wing has an upper surface, a lower surface, a forward region with a leading edge, and an aft region with a trailing edge; a passenger cabin positioned within the aft portion of the fuselage, the passenger cabin having first, second, third, and fourth passenger seat sections, with each of the first, second, third, and fourth seat sections having at least two passenger seats abreast and with neighboring passenger seat sections being spaced apart from each other to form first, second, and third passenger aisles positioned at least generally parallel to the longitudinal axis of the fuselage; and a propulsion system at least proximate to the aft region of the wing, with at least part of the propulsion system positioned between the upper and lower surfaces of the wing, the propulsion system having at least one inlet aperture positioned beneath the wing lower surface or above the wing upper surface, at least one engine positioned aft of and vertically offset from the at least one inlet aperture, and at least one exhaust nozzle aft of the at least one engine, wherein the wing and the propulsion system are configured to operate at a cruise Mach number ranging from about 0.90 to about 0.96. 48. The aircraft of claim 46 further comprising: a cargo hold positioned within the aft portion of the fuselage; a fuel volume positioned within the wing and configured to carry fuel; and a center of gravity through which the resultant of the gravitational forces on all components of the aircraft acts, the center of gravity having a first position when the fuel volume is approximately full of fuel and a second position when the fuel volume is approximately empty of fuel, the first and second positions being located within the cargo hold. 49. The aircraft of claim 46 wherein the aft portion of the fuselage further includes an upper fuselage surface spaced apart from a lower fuselage surface, wherein the wing extends from the fuselage between the upper and lower fuselage surfaces adjacent to the aft portion of the fuselage, and wherein the aircraft further comprises: at least a first window positioned in the upper fuselage surface directly adjacent the first passenger seat section; and at least a second window positioned in the upper fuselage surface directly adjacent the fourth passenger seat section. 50. The aircraft of claim 46 wherein the aft portion of the fuselage has a generally oval cross-sectional shape and the passenger cabin has a width of between about 25 feet and about 35 feet. 51. An aircraft comprising: a fuselage configured to carry a payload and having a longitudinal axis, the fuselage having a forward portion and an aft portion, the aft portion defining a generally constant-width planform; a wing extending from the fuselage adjacent to the aft portion of the fuselage; a passenger cabin positioned within the aft portion of the fuselage, the passenger cabin having first, second, third, and fourth passenger seat sections, with each of the first, second, third, and fourth seat sections having at least two passenger seats abreast and with neighboring passenger seat sections being spaced apart from each other to form first, second, and third passenger aisles positioned at least generally parallel to the longitudinal axis of the fuselage; a cargo hold configured to hold cargo and positioned within the aft portion of the fuselage; and a center of gravity through which the resultant of the gravitational forces on all components of the aircraft acts, the center of gravity being positioned within the cargo hold. 52. The aircraft of claim 51 wherein each of the first, second, third, and fourth seat sections includes at least 54 passenger seats. 53. The aircraft of claim 51 wherein each of the first, second, third, and fourth passenger seat sections includes a portion having three seats abreast and extending for at least 14 contiguous rows. 54. An aircraft comprising: a fuselage configured to carry a payload and having a longitudinal axis, the fuselage having a forward portion and an aft portion, the aft portion defining a generally constant-width planform; a wing extending from the fuselage adjacent to the aft portion of the fuselage, wherein the wing has an upper surface, a lower surface, a forward region with a leading edge, and an aft region with a trailing edge; a passenger cabin positioned within the aft portion of the fuselage, the passenger cabin having first, second, third, and fourth passenger seat sections, with each of the first, second, third, and fourth seat sections having at least two passenger seats abreast and with neighboring passenger seat sections being spaced apart from each other to form first, second, and third passenger aisles positioned at least generally parallel to the longitudinal axis of the fuselage; a cargo hold configured to hold cargo and positioned within the aft portion of the fuselage; a center of gravity through which the resultant of the gravitational forces on all components of the aircraft acts, the center of gravity being positioned within the cargo hold; and a propulsion system at least proximate to the aft region of the wing, with at least part of the propulsion system positioned between the upper and lower surfaces of the wing, the propulsion system having at least one inlet aperture positioned beneath the wing lower surface or above the wing upper surface, at least one engine positioned aft of and vertically offset from the at least one inlet aperture, and at least one exhaust nozzle aft of the at least one engine, wherein the wing and the propulsion system are configured to operate at a cruise Mach number ranging from about 0.90 to about 0.96. 55. The aircraft of claim 51 wherein the wing has a delta planform. 56. The aircraft of claim 51 further comprising a fuel volume positioned within the wing and configured to carry fuel, wherein the center of gravity has a first position when the fuel volume is approximately full of fuel and a second position when the fuel volume is approximately empty of fuel, the first and second positions being located within the cargo hold. 57. The aircraft of claim 51 wherein the aft portion of the fuselage includes an upper fuselage surface spaced apart from a lower fuselage surface, wherein the aft portion of the fuselage further includes a cargo hold door configured to facilitate loading of cargo into the cargo hold, the cargo hold door being operably integrated with the lower surface of the aft portion of the fuselage along the longitudinal axis of the fuselage. 58. The aircraft of claim 51 wherein the cargo hold has a width of greater than 10 feet and a length of greater than 25 feet. 59. The aircraft of claim 58 wherein the cargo hold has a width of between about 25 feet and about 35 feet, and a length of between about 35 feet and about 45 feet. 60. The aircraft of claim 58 wherein the aircraft further comprises a propulsion system, wherein the wing and the propulsion system are configured to operate at a cruise Mach number ranging from about 0.90 to about 0.96, and wherein the cargo hold has a width of between about 25 feet and about 35 feet, and a length of between about 35 feet and about 45 feet. 61. The aircraft of claim 51 wherein the cargo hold is configured to hold at least 12 Unit Load Device LD-3 cargo containers. 62. The aircraft of claim 51 wherein the cargo hold can accommodate up to four Unit Load Device LD-3 cargo containers positioned abreast. 63. The aircraft of claim 51 wherein the cargo hold has a length greater than about 20 percent of the fuselage length. 64. The aircraft of claim 51 wherein the cargo hold has a width greater than about 18 percent of the wing span. 65. An aircraft comprising: a fuselage configured to carry a payload and having a longitudinal axis, the fuselage having a forward portion and an aft portion, the aft portion defining a generally constant-width planform; a wing extending from the fuselage adjacent to the aft portion of the fuselage, the wing having a forward region with a leading edge and an aft region with a trailing edge, the wing further having an upper surface and a lower surface; a propulsion system at least proximate to the aft region of the wing, with at least part of the propulsion system positioned between the upper and lower surfaces of the wing, the propulsion system having at least one inlet aperture positioned beneath the wing lower surface or above the wing upper surface, at least one engine positioned aft of and vertically offset from the at least one inlet aperture, and at least one exhaust nozzle aft of the at least one engine; a passenger cabin positioned within the aft portion of the fuselage, the passenger cabin having first, second, third, and fourth passenger seat sections, with each of the first, second, third, and fourth seat sections having at least two passenger seats abreast and with neighboring passenger seat sections being spaced apart from each other to form first, second, and third passenger aisles positioned at least generally parallel to the longitudinal axis of the fuselage; a cargo hold configured to hold cargo and positioned within the aft portion of the fuselage; and a center of gravity through which the resultant of the gravitational forces on all components of the aircraft acts, the center of gravity being located within the cargo hold. 66. The aircraft of claim 65 wherein each of the first, second, third, and fourth seat sections includes at least 54 passenger seats. 67. The aircraft of claim 65 wherein each of the first, second, third, and fourth passenger seat sections includes a portion having three seats abreast and extending for at least 14 contiguous rows. 68. The aircraft of claim 65 wherein the wing and the propulsion system are configured to operate at a cruise Mach number ranging from about 0.90 to about 0.96. 69. The aircraft of claim 65 wherein the wing has a delta planform. 70. The aircraft of claim 65 further comprising a fuel volume positioned within the wing and configured to carry fuel, wherein the center of gravity has a first position when the fuel volume is approximately full of fuel and a second position when the fuel volume is approximately empty of fuel, the first and second positions being located within the cargo hold. 71. The aircraft of claim 65 wherein the aft portion of the fuselage further includes an upper fuselage surface spaced apart from a lower fuselage surface, wherein the wing extends from the fuselage between the upper and lower fuselage surfaces adjacent to the aft portion of the fuselage, and wherein the aircraft further comprises: at least a first window positioned in the upper fuselage surface directly adjacent the first passenger seat section; and at least a second window positioned in the upper fuselage surface directly adjacent the fourth passenger seat section. 72. The aircraft of claim 65 further comprising: a generally horizontal and moveable first control surface integrated with the fuselage adjacent to the aft portion of the fuselage; and a generally horizontal and moveable second control surface integrated with the aft region of the wing outboard of the at least one engine. 73. The aircraft of claim 65 wherein the aft portion of the fuselage has a generally oval cross-sectional shape and a width of about 29 feet. 74. The aircraft of claim 65 wherein the aft portion of the fuselage has an upper interior surface and a lower interior surface and a floor portion extending horizontally between the upper interior surface and the lower interior surface to separate the passenger cabin from the cargo hold, and wherein the passenger cabin is absent any load-bearing member extending vertically between the floor portion and the upper interior surface between the seat sections. 75. The aircraft of claim 65 wherein the wing includes a fuel volume configured to carry fuel for the propulsion system, and wherein the engine includes rotating components, further wherein the rotating components of the engine are positioned aft of the fuel volume. 76. The aircraft of claim 65 wherein the wing includes a fuel volume configured to carry fuel for the propulsion system, and wherein the engine includes rotating components, further wherein the rotating components of the engine are positioned aft of the fuel volume and the passenger cabin. 77. The aircraft of claim 65 wherein the fuselage has a nose end and a tail end, wherein the forward portion of the fuselage extends forward directly from the aft portion defining a generally continuously monotonically tapering planform between the aft portion and the nose end, and the aft portion extends aft directly from the forward portion defining a generally constant-width planform between the forward portion and the tail end. 78. The aircraft of claim 65 wherein the wing and the propulsion system are configured to operate at a cruise Mach number ranging from about 0.90 to about 0.96, and wherein the cargo hold has a width of between about 25 feet and about 30 feet and a length of between about 35 feet and about 43 feet. 79. A method for manufacturing an aircraft, the method comprising: attaching a wing to a fuselage having a longitudinal axis, a forward portion, and an aft portion, the aft portion defining a generally constant-width planform, the wing having an upper surface, a lower surface, a forward region with a leading edge, and an aft region with a trailing edge; and positioning a passenger cabin within the aft portion of the fuselage adjacent to the wing, the passenger cabin having first, second, third, and fourth passenger seat sections, with each of the first, second, third, and fourth seat sections having at least three passenger seats abreast extending for at least 14 contiguous rows, with neighboring passenger seat sections being spaced apart from each other to form first, second, and third passenger aisles positioned at least generally parallel to the longitudinal axis of the fuselage. 80. The method of claim 79 wherein positioning the passenger cabin within the aft portion of the fuselage includes installing at least 54 passenger seats in each of the first, second, third, and fourth seat sections. 81. A method for manufacturing an aircraft, the method comprising: attaching a wing to a fuselage having a longitudinal axis, a forward portion, and an aft portion, the aft portion defining a generally constant-width planform, the wing having an upper surface, a lower surface, a forward region with a leading edge, and an aft region with a trailing edge; positioning a passenger cabin within the aft portion of the fuselage adjacent to the wing, the passenger cabin having first, second, third, and fourth passenger seat sections, with each of the first, second, third, and fourth seat sections having at least two passenger seats abreast and with neighboring passenger seat sections being spaced apart from each other to form first, second, and third passenger aisles positioned at least generally parallel to the longitudinal axis of the fuselage; and coupling a propulsion system at least proximate to the aft region of the wing, with at least part of the propulsion system positioned between the upper and lower surfaces of the wing, the propulsion system having at least one inlet aperture positioned beneath the wing lower surface or above the wing upper surface, at least one engine positioned aft of and vertically offset from the at least one inlet aperture, and at least one exhaust nozzle aft of the at least one engine. 82. The method of claim 81 further comprising configuring the wing and the propulsion system to operate at a cruise Mach number ranging from about 0.80 to about 0.98. 83. The method of claim 81 further comprising configuring the wing and the propulsion system to operate at a cruise Mach number ranging from about 0.90 to about 0.96. 84. The method of claim 80 further comprising positioning a cargo hold within the aft portion of the fuselage, wherein a center of gravity through which the resultant of the gravitational forces on all components of the aircraft acts is positioned within the cargo hold. 85. The method of claim 80 further comprising: positioning a cargo hold within the aft portion of the fuselage, wherein a center of gravity through which the resultant of the gravitational forces on all components of the aircraft acts is positioned within the cargo hold; and positioning a fuel volume within the wing, the fuel volume configured to carry fuel for the at least one engine, wherein the center of gravity has a first position when the fuel volume is approximately full of fuel and a second position when the fuel volume is approximately empty of fuel, the first and second positions being located within the cargo hold. 86. The method of claim 80 wherein the aft portion of the fuselage further includes an upper fuselage surface spaced apart from a lower fuselage surface, wherein the wing extends from the fuselage between the upper and lower fuselage surfaces adjacent to the aft portion of the fuselage, and wherein the method further comprises: positioning at least a first window in the upper fuselage surface directly adjacent the first passenger seat section; and positioning at least a second window in the upper fuselage surface directly adjacent the fourth passenger seat section. 87. The method of claim 80 further comprising: positioning a cargo hold within the aft portion of the fuselage, wherein a center of gravity through which the resultant of the gravitational forces on all components of the aircraft acts is positioned within the cargo hold; and operably integrating a cargo hold door with a lower surface of the aft portion of the fuselage along the longitudinal axis of the fuselage, the cargo hold door configured to facilitate loading of cargo into the cargo hold. 88. The method of claim 80 wherein the engine includes rotating components, the method further comprising: positioning a fuel volume in the wing, the fuel volume configured to carry fuel for the propulsion system; and positioning the rotating components of the engine aft of the fuel volume and the passenger cabin. 89. The method of claim 80 wherein attaching the wing to the fuselage includes mounting the wing to the fuselage adjacent to the aft portion of the fuselage. 90. An aircraft comprising: a fuselage having a forward portion and an aft portion aligned along a longitudinal axis, the aft portion defining a generally constant-width planform; a wing extending from the fuselage adjacent to the aft portion of the fuselage; a passenger cabin positioned within the aft portion of the fuselage, the passenger cabin having first, second, third, and fourth passenger seat sections, with each of the first, second, third, and fourth seat sections having at least two passenger seats abreast and with neighboring passenger seat sections being spaced apart from each other to form first, second, and third passenger aisles positioned at least generally parallel to the longitudinal axis of the fuselage; and a propulsion system positioned at least proximate to the wing, the propulsion system having at least one inlet aperture and at least one engine positioned aft of and vertically offset from the at least one inlet aperture. 91. The aircraft of claim 90 wherein the wing includes an upper surface, a lower surface, a forward region with a leading edge, and an aft region with a trailing edge, wherein the propulsion system is positioned at least proximate to the aft region of the wing, and wherein the at least one inlet aperture is positioned beneath the wing lower surface or above the wing upper surface. 92. An aircraft comprising: a fuselage having a forward portion and an aft portion aligned along a longitudinal axis, the aft portion defining a generally constant-width planform; a wing extending from the fuselage adjacent to the aft portion of the fuselage, wherein the wing has an upper surface and a lower surface; a passenger cabin positioned within the aft portion of the fuselage, the passenger cabin having first, second, third, and fourth passenger seat sections, with each of the first, second, third, and fourth seat sections having at least two passenger seats abreast and with neighboring passenger seat sections being spaced apart from each other to form first, second, and third passenger aisles positioned at least generally parallel to the longitudinal axis of the fuselage; and a propulsion system positioned at least proximate to the wing, with at least part of the propulsion system positioned between the upper and lower surfaces of the wing. 93. The aircraft of claim 92 wherein the wing further includes a forward region with a leading edge and an aft region with a trailing edge, and wherein the propulsion system is positioned at least proximate to the aft region of the wing. 94. The aircraft of claim 3 wherein the wing has a forward region with a leading edge, the leading edge having a first part proximate to the fuselage with a first sweep angle and a second part outboard of the first part with a second sweep angle less than the first sweep angle. 95. The aircraft of claim 3 further comprising: a cargo hold positioned within the aft portion of the fuselage; and a center of gravity through which the resultant of the gravitational forces on all components of the aircraft acts, the center of gravity having a position within the cargo hold. 96. The aircraft of claim 3 wherein the aft portion of the fuselage further includes an upper fuselage surface spaced apart from a lower fuselage surface, wherein the wing extends from the fuselage between the upper and lower fuselage surfaces adjacent to the aft portion of the fuselage, and wherein the aircraft further comprises: at least a first window positioned in the upper fuselage surface directly adjacent the first passenger seat section; and at least a second window positioned in the upper fuselage surface directly adjacent the fourth passenger seat section. 97. The aircraft of claim 3 further comprising a generally horizontal and moveable elevator surface adjacent to the aft portion of the fuselage. 98. The aircraft of claim 3 wherein the fuselage is configured to carry a commercial passenger payload of at least 230 passengers and/or a commercial cargo payload. 99. The aircraft of claim 4 wherein each of the first, second, third, and fourth seat sections includes at least 54 passenger seats. 100. The aircraft of claim 16 wherein each of the first, second, third, and fourth seat sections includes at least 54 passenger seats. 101. The aircraft of claim 16 wherein the wing has a delta planform.
