There is disclosed an aircraft including a fuselage extending along a longitudinal axis; forward swept wings extending from the fuselage; at least one horizontal stabilizer secured to the fuselage; and a distributed electrical propulsion system operatively connected to an electrical power source. The distributed electrical propulsion system have an air intake located rearward of an intersection between the forward swept wings and the fuselage open to a boundary layer region on a surface of the fuselage.
FORWARD SWEPT WING AIRCRAFT WITH BOUNDARY LAYER INGESTION AND DISTRIBUTED ELECTRICAL PROPULSION SYSTEM
2020-06-18
Patent
Electronic Resource
English
European Patent Office | 2020
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