CPC B64C 21/01 (2023.01) [B64C 21/06 (2013.01); B64C 39/10 (2013.01); B64D 29/00 (2013.01); B64D 29/04 (2013.01); B64C 2039/105 (2013.01); B64D 2033/0226 (2013.01)] | 20 Claims |
1. An apparatus for ingesting boundary layer flow on an aircraft, wherein the apparatus comprises:
a blended wing body, wherein the blended wing body is characterized by having no clear dividing line between wings and main body of the aircraft;
a nacelle located aft of a leading edge of the blended wing body, wherein the nacelle further comprises:
a propulsor configured to propel the aircraft; and
a primary duct, wherein the primary duct is configured to intake an airflow from a forward portion of the nacelle to a rear portion of the nacelle; and
a flow augmentation arrangement, wherein the flow augmentation arrangement is configured to accelerate a boundary layer flow in the airflow, wherein the flow augmentation arrangement further comprises:
a secondary duct, wherein the secondary duct is configured to ingest the boundary layer flow in the airflow from an inlet proximal to the forward portion of the nacelle to an outlet proximal to the rear portion of the nacelle; and
a tertiary duct connecting the primary duct to the secondary duct, wherein the tertiary duct comprises an extended section located within the secondary duct.
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