An aircraft 10 comprises a propulsion arrangement 50 comprising first and second propulsors 2 and 3. The first propulsor 2 comprises an inlet (29, Fig 2) and an exhaust (35, Fig 2) upstream of an inlet (37, Fig 2) of the second propulsor 3 such that an exhaust of the first propulsor is ingested by the second propulsor. The first propulsor has an inlet area less than an inlet area of the second propulsor and is arranged to ingest at least part of a boundary layer flow adjacent a surface 13 of the aircraft.
Aircraft comprising a boundary layer ingesting propulsor
15.03.2017
Patent
Elektronische Ressource
Englisch
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