Apparatus for ingesting boundary layer flow for an aircraft

An apparatus for ingesting boundary layer flow on an aircraft, wherein the apparatus comprises:

• a nacelle configured to house at least a portion of a plurality of flight components, wherein the nacelle comprises:
• a propulsor, wherein the propulsor is configured to propel the aircraft;
• and
• a primary duct, wherein the primary duct is configured to intake an airflow from a first portion of the nacelle to a second 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 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 first portion of the nacelle to an outlet proximal to the second 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.