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.


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    Title :

    SUPERSONIC CARET INLET SYSTEM


    Additional title:

    ÜBERSCHALL-EINLASSSYSTEM MIT CARET
    SYSTÈME D'ENTRÉE DE CARET SUPERSONIQUE


    Contributors:
    HUYNH THUY (author)

    Publication date :

    2020-04-01


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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