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A scarf nozzle for a jet engine supported within a nacelle. The scarf nozzle is at an aft end of the nacelle. The scarf nozzle includes a first trailing edge portion and a second trailing edge portion. The second trailing edge portion is disposed aft of the first trailing edge portion. The scarf noz

A scarf nozzle for a jet engine supported within a nacelle. The scarf nozzle is at an aft end of the nacelle. The scarf nozzle includes a first trailing edge portion and a second trailing edge portion. The second trailing edge portion is disposed aft of the first trailing edge portion. The scarf nozzle is configured to allow the nacelle to be integrated closer to a wing without adversely affecting the pressure gradient between the nacelle and the wing. The scarf nozzle allows a portion of an exhaust plume exiting the aft end of the nacelle to interact more favorably with an airflow along one or more surfaces adjacent the nacelle, thus delaying the onset of adverse pressure gradients and the formation of shock waves between the nacelle and the adjacent surfaces and between the adjacent surfaces and the exhaust plume.

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1. A jet engine for a mobile platform, the jet engine comprising:a housing having a fore end and an aft end; and a scarf nozzle at the aft end of the housing, the scarf nozzle including a first trailing edge portion and a second trailing edge portion disposed aft of the first trailing edge portion,

1. A jet engine for a mobile platform, the jet engine comprising:a housing having a fore end and an aft end; and a scarf nozzle at the aft end of the housing, the scarf nozzle including a first trailing edge portion and a second trailing edge portion disposed aft of the first trailing edge portion, the scarf nozzle being configured to at least mitigate an adverse wing pressure gradient increase between the housing and a wing surface of the mobile platform and between the wing surface and an exhaust plume exiting the aft end of the housing to enable the housing to be positioned closer to the wing surface. 2. The jet engine of claim 1, wherein the housing comprises a nacelle.3. The jet engine of claim 2, wherein the scarf nozzle is configured to allow at least a portion of an exhaust plume exiting the aft end of the nacelle to interact more favorably with a fluid flow along one or more surfaces adjacent the nacelle.4. The jet engine of claim 2, wherein:the first trailing edge portion comprises an upper portion of the scarf nozzle; and the second trailing edge portion comprises a lower portion of the scarf nozzle. 5. The jet engine of claim 2, wherein the scarf nozzle comprises a plurality of chevrons configured to allow substantial mixing of at least a portion of an exhaust gas exiting the aft end of the nacelle with ambient air adjacent the scarf nozzle.6. The jet engine of claim 2, further comprising a noise attenuating material lining at least a portion of an inner surface of the scarf nozzle.7. The jet engine of claim 2, wherein a rear-most edge of the scarf nozzle is disposed at a bottommost trailing edge position of the scarf nozzle.8. The jet engine of claim 2, wherein the scarf nozzle is configured to at least delay formation of shock waves between the nacelle and a wing surface adjacent the nacelle.9. The jet engine of claim 2, wherein the scarf nozzle is configured to at least delay formation of shock waves between the exhaust plume and a wing surface adjacent the nacelle.10. The jet engine of claim 2, wherein the scarf nozzle is configured to at least mitigate an adverse pressure gradient increase caused by the nacelle and the exhaust plume.11. The jet engine of claim 2, wherein the scarf nozzle is configured to at least partially shield engine noise from being transmitted downward.12. The jet engine of claim 2, wherein scarf nozzle is controllably rotatable relative to the nacelle to a plurality of angular positions during different phases of operation of the mobile platform.13. The jet engine of claim 12, wherein the scarf nozzle is rotatable to dispose a rear-most edge of the scarf nozzle at at least one of:a topmost position of the scarf nozzle; a bottommost position of the scarf nozzle; an outboard position of the scarf nozzle; and a an inboard position of the scarf nozzle. 14. The jet engine of claim 12, wherein the scarf nozzle is rotatable to at least one of:a configuration in which the scarf nozzle imparts a downward vector to the exhaust plume; a configuration in which the scarf nozzle imparts an upward vector to the exhaust plume; a configuration in which the scarf nozzle imparts an outboard vector to the exhaust plume; and a configuration in which the scarf nozzle imparts an inboard vector to the exhaust plume. 15. The jet engine of claim 2, wherein the mobile platform comprises an aircraft.16. The jet engine of claim 1, wherein an interior of the scarf nozzle is configured such that a velocity vector of the exhaust plume exiting the aft end of the housing is generally straight aft.17. The jet engine of claim 1, wherein an interior of the scarf nozzle is configured to direct the exhaust plume to at least mitigate the exhaust plume from exiting the scarf nozzle adjacent the first trailing edge portion prior to reaching the second trailing edge portion.18. The jet engine of claim 17, wherein the scarf nozzle includes a nozzle throat defining a generally slanted plane.19. An aircraft, comprising:a wing-mounted jet engine; a nacelle for housing the jet engine, the nacelle being used to house the jet engine and including a fore end and an aft end; and a scarf nozzle at the aft end of the nacelle, the scarf nozzle including a first trailing edge portion and a second trailing edge portion disposed aft of the first trailing edge portion, the scarf nozzle being configured to at least mitigate an adverse wing pressure gradient increase between the nacelle and a wing surface of the aircraft and between the wing surface and an exhaust plume exiting the aft end of the nacelle to enable the nacelle to be positioned closer to the wing surface. 20. The aircraft of claim 19, wherein the scarf nozzle is configured to allow at least a portion of an exhaust plume exiting the aft end of the nacelle to interact more favorably with a fluid flow along one or more surfaces adjacent the scarf nozzle.21. The aircraft of claim 19, wherein:the first trailing edge portion comprises an upper portion of the scarf nozzle; and the second trailing edge portion comprises a lower portion of the scarf nozzle. 22. The aircraft of claim 19, wherein the scarf nozzle comprises a plurality of chevrons configured to allow substantial mixing of at least a portion of an exhaust gas exiting the aft end of the nacelle with ambient air adjacent the scarf nozzle.23. The aircraft of claim 19, further comprising a noise attenuating material lining at least a portion of an inner surface of the scarf nozzle.24. The aircraft of claim 19, wherein a rear-most edge of the scarf nozzle is disposed at a bottommost trailing edge position of the scarf nozzle.25. The aircraft of claim 19, wherein the scarf nozzle is configured to at least delay formation of shock waves between the nacelle and a wing surface adjacent the nacelle.26. The aircraft of claim 19, wherein the scarf nozzle is configured to at least delay a formation of a shock wave between a wing surface adjacent the nacelle and an exhaust plume exiting the aft end of the nacelle.27. The aircraft of claim 19, wherein the scarf nozzle is configured to at least mitigate an increase in an adverse pressure gradient caused by the nacelle and an exhaust plume exiting the aft end of the nacelle.28. The aircraft of claim 19, wherein the scarf nozzle is configured to at least partially shield engine noise from being transmitted downward.29. The aircraft of claim 19, wherein the scarf nozzle is controllably rotatable relative to the nacelle to a plurality of angular positions during different phases of operation of the aircraft.30. The aircraft of claim 29, wherein the scarf nozzle is rotatable to dispose a rear-most edge of the scarf nozzle at at least one of:a topmost position of the scarf nozzle; a bottommost position of the scarf nozzle; an outboard position of the scarf nozzle; and a an inboard position of the scarf nozzle. 31. The aircraft of claim 29, wherein the scarf nozzle is rotatable to at least one of:a configuration in which the scarf nozzle imparts a downward vector to the exhaust plume; a configuration in which the scarf nozzle imparts an upward vector to the exhaust plume; a configuration in which the scarf nozzle imparts an outboard vector to the exhaust plume; and a configuration in which the scarf nozzle imparts an inboard vector to the exhaust plume. 32. The aircraft of claim 19, wherein an interior of the scarf nozzle is configured such that a velocity vector of the exhaust plume exiting the aft end of the nacelle is generally straight aft.33. The aircraft of claim 19, wherein an interior of the scarf nozzle is configured to direct the exhaust plume to at least mitigate the exhaust plume from exiting the scarf nozzle adjacent the first trailing edge portion prior to reaching the second trailing edge portion.34. The aircraft of claim 33, wherein the scarf nozzle includes a nozzle throat defining a generally slanted plane.