SWEPT GRADIENT BOUNDARY LAYER DIVERTER

摘要

A swept gradient air boundary layer diverter for an aircraft. The aircraft includes a fuselage and an air inlet for an engine of the aircraft, where the air inlet includes a cowl at a leading edge of the inlet. The diverter includes a V-shaped ramp portion formed in the fuselage in an area proximate to and in front of the cowl where the ramp portion extends downward away from an outer surface of the fuselage towards an inside of the aircraft. The diverter also includes a V-shaped trough portion formed into the fuselage and being positioned adjacent to and integral with the ramp portion between the ramp portion and the air inlet. Air flowing over the fuselage towards the cowl is expanded and compressed by the ramp portion and the trough portion so as to create pressure gradients that generate vortices to redirect boundary layer airflow around the air inlet.

主权项

1. An air boundary layer diverter for an aircraft, said aircraft including a fuselage and at least one engine air inlet for an engine of the aircraft, said engine air inlet including a shaped cowl at a leading edge of the engine air inlet defining an opening through which air flows to the engine, said diverter comprising:
a ramp portion formed in the fuselage in an area proximate to and in front of the cowl where the ramp portion extends downward away from an outer surface of the fuselage towards an inside of the aircraft; and a trough portion formed in the fuselage and being positioned adjacent to and integral with the ramp portion between the ramp portion and the engine air inlet, wherein air flowing over the fuselage towards the cowl is expanded and compressed by the ramp portion and the trough portion so as to create pressure gradients that generate vortices to direct a boundary layer airflow away from and around the air inlet.