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An inlet for an aircraft engine nacelle having an acoustic barrel panel, a septum buried or sandwiched within the acoustic barrel panel, and a perforated face sheet. The inlet may be located forward of an engine and/or an engine fan housed within the aircraft engine nacelle. Both the septum and the

An inlet for an aircraft engine nacelle having an acoustic barrel panel, a septum buried or sandwiched within the acoustic barrel panel, and a perforated face sheet. The inlet may be located forward of an engine and/or an engine fan housed within the aircraft engine nacelle. Both the septum and the perforated face sheet may have perforations or holes therein of varying sizes and varying distances apart from each other. The smaller the area of the perforations or holes and the further apart they are from each other, the higher the impedance of a given area of the septum or the perforated face sheet. The impedance of the septum and/or the perforated face sheet may progressively increase in a direction away from the engine fan.

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1. An aircraft engine nacelle inlet comprising: an acoustic barrel panel having an outer surface, an inner surface, a forward end, and an aft end;a septum sandwiched or buried within the acoustic barrel panel, wherein the septum has a plurality of holes formed therein of varying dimensional areas an

1. An aircraft engine nacelle inlet comprising: an acoustic barrel panel having an outer surface, an inner surface, a forward end, and an aft end;a septum sandwiched or buried within the acoustic barrel panel, wherein the septum has a plurality of holes formed therein of varying dimensional areas and/or varying proximities relative to each other; anda face sheet bonded to the inner surface of the acoustic barrel panel, spaced a distance apart from the septum, and having a plurality of holes formed therein of varying dimensional areas and/or varying proximities relative to each other,wherein acoustical impedance of at least one of the face sheet and the septum is incrementally increased in a direction from the aft end toward the forward end of the acoustic barrel panel by at least one of incrementally decreasing the dimensional areas of the holes and incrementally increasing the proximities of the holes relative to each other. 2. The inlet of claim 1, further comprising: an outer barrel panel having a forward end and an aft end, wherein the outer barrel panel is spaced a distance apart from the acoustic barrel panel;a forward bulkhead joining the forward end of the acoustic barrel panel with the forward end of the outer barrel panel, andan aft bulkhead joining the aft end of the acoustic barrel panel with the aft end of the outer barrel panel, wherein at least one of the outer barrel panel and the aft bulkhead is configured to attach to a fan cowl of the aircraft engine nacelle. 3. The inlet of claim 2, further comprising a lip skin attached to and located forward of the forward bulkhead. 4. The inlet of claim 1, further comprising an impervious back sheet bonded to the outer surface of the acoustic barrel panel. 5. The inlet of claim 1, wherein the acoustic barrel panel is a honeycomb acoustic panel having a plurality of cell walls cooperatively forming an array of hexagonal shaped cells or openings therebetween. 6. An aircraft engine nacelle inlet comprising: an acoustic barrel panel having an outer surface, an inner surface, a forward end, and an aft end, wherein the acoustic barrel panel further comprises a plurality of cell walls cooperatively forming an array of hexagonal shaped cells or openings therebetween;a septum sandwiched or buried within the acoustic barrel panel between the outer and inner surface, wherein the septum has a plurality of holes formed therein having varying dimensional areas and varying proximities relative to each other depending on a proximity of the holes to the aft end of the acoustic barrel panel; anda face sheet bonded to the inner surface of the acoustic barrel panel, spaced a distance apart from the septum, and having a plurality of holes formed therein of varying dimensional areas and varying proximities relative to each other depending on a proximity of the holes to the aft end of the acoustic barrel panel,wherein at least one of the dimensional areas of the holes in the face sheet incrementally decrease and the distance apart of the holes in the face sheet relative to each other incrementally increase in a direction from the aft end toward the forward end of the acoustic barrel panel, orwherein at least one of the dimensional areas of the holes in the septum incrementally decrease and the distance apart of the holes in the septum relative to each other incrementally increase in a direction from the aft end toward the forward end of the acoustic barrel panel. 7. The inlet of claim 6, further comprising: an outer barrel panel having a forward end and an aft end, wherein the outer barrel panel is spaced a distance apart from the acoustic barrel panel;a forward bulkhead joining the forward end of the acoustic barrel panel with the forward end of the outer barrel panel, andan aft bulkhead joining the aft end of the acoustic barrel panel with the aft end of the outer barrel panel, wherein at least one of the outer barrel panel and the aft bulkhead is configured to attach to a fan cowl of the aircraft engine nacelle. 8. The inlet of claim 6, wherein the septum is divided into two or more impedance zones, wherein the impedance zones closer to the aft end of the acoustic barrel panel have holes that are at least one of larger in dimensional area and closer in proximity to each other than the holes of the impedance zones closer to the forward end of the acoustic barrel panel. 9. An aircraft engine nacelle inlet comprising: an inner acoustic panel having a forward end and an aft end, the inner acoustic panel including: an acoustic barrel panel having an outer surface, an inner surface, a forward end, and an aft end, wherein the acoustic barrel panel further comprises a plurality of cell walls cooperatively forming an array of hexagonal shaped cells or openings therebetween,a septum sandwiched or buried within the acoustic barrel panel between the outer and inner surface, wherein the septum has a plurality of holes formed therein having varying areas and varying proximities relative to each other depending on a proximity of the holes to the aft end of the acoustic barrel panel, wherein at least one of the dimensional areas of the holes in the septum incrementally decrease and the distance apart of the holes in the septum relative to each other incrementally increase in a direction from the aft end toward the forward end of the acoustic barrel panel, anda face sheet bonded to the inner surface of the acoustic barrel panel, spaced a distance apart from the septum, and having a plurality of holes formed therein of varying areas and varying proximities relative to each other depending on a proximity of the holes to the aft end of the acoustic barrel panel;an outer barrel panel having a forward end and an aft end, wherein the outer barrel panel is spaced a distance apart from the inner acoustic panel;a forward bulkhead joining the forward end of the inner acoustic panel with the forward end of the outer barrel panel; andan aft bulkhead joining the aft end of the inner acoustic panel with the aft end of the outer barrel panel, wherein at least one of the outer barrel panel and the aft bulkhead is configured to attach to a fan cowl of the aircraft engine nacelle. 10. The inlet of claim 9, wherein at least one of the dimensional areas of the holes in the face sheet incrementally decrease and the distance apart of the holes in the face sheet relative to each other incrementally increase in a direction from the aft end toward the forward end of the acoustic barrel panel.