Automatic boundary layer control in an ejector wing aircraft
AssigneeThe United States of America as represented by the Secretary of the Air Force
InventorHermann Viets
Life of this patent
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Abstract
An ejector wing, for an aircraft, having inlet and diffuser doors which move from an open take-off configuration to a closed forward flight configuration and having hypermixing nozzles and root nozzles for supplying primary air into a plurality of channels in the wing structure. Apparatus is provided for controlling the air flow from the root nozzles in the boundary layer in the channels. A plurality of sensing ports are provided in the channels upstream of the root nozzles. The differential pressures at the sensing ports are used to divide the flow to the root nozzles on opposite sides of the channels.
Claims3
In an aircraft ejector wing having a plurality of spar members with air flow thrust channel being formed between pairs of spar members;
- means for providing closable inlets to said flow thrust channels;
- means for providing closable outlet diffuser doors for said thrust channels;
- means for providing a primary air flow through said thrust channels to thereby entrain a secondary flow through the thrust channels;
- said means for providing a primary air flow including a plurality of nozzles adapted to provide a flow of air into the boundary layer adjacent the opposite sides of said thrust channels;
- a plurality of pressure sensing ports in said thrust channels upstream of said nozzles;
- means responsive to the pressure at said sensing ports for controlling the flow from said nozzles into the boundary layer in said thrust channels.
Dependencies are inferred from the claim text.