An engine inlet (10) for efficient operation in both subsonic and supersonic flight wherein the inlet has a caret configuration, is rotatable about an off-body axis (30) for compression ramp angle and capture area variation and a diffuser (14) is engaged to the inlet in a scrubbing relationship to maintain a seal upon rotation of the inlet.
SUPERSONIC CARET INLET SYSTEM
ÜBERSCHALL-EINLASSSYSTEM MIT CARET
SYSTÈME D'ENTRÉE DE CARET SUPERSONIQUE
2020-04-01
Patent
Electronic Resource
English
European Patent Office | 2022
European Patent Office | 2017
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