An inlet for a flight vehicle engine, such as for a supersonic or hypersonic engine, includes an internal flow diverter to divert boundary layer flow. The flow diverter is configured to minimize disruption to flow outside the diverted boundary by being configured through use of a flow field that is also used to configure the walls of the inlet. The flow field that is used to configure an inlet-creating shape and a diverter-creating shape has the same flow generator, contraction ratio, compression ratio, mass capture ratio, pressure ratio between entrance and exit, and/or Mach number, for example. The internal diverter may be configured so as to allow arbitrary selection of a leading edge shape for the internal diverter, for example to use a shape that helps avoid radar detection.


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    Titel :

    METHOD OF CONFIGURING A FLIGHT VEHICLE ENGINE INLET WITH INTERNAL DIVERTER


    Weitere Titelangaben:

    KONFIGURATIONSVERFAHREN EINES FLUGZEUGMOTOREINLASSES MIT INTERNER UMLENKVORRICHTUNG
    PROCÉDÉ DE CONFIGURATION D'UNE ENTRÉE DE MOTEUR DE VÉHICULE VOLANT COMPRENANT UN DÉFLECTEUR INTERNE


    Beteiligte:

    Erscheinungsdatum :

    26.02.2025


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS



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