Jet engine inlet structure of a supersonic aircraft comprising the structure having an inlet ramp and an cowl lip spaced outwardly of the ramp so that entering air flows between the ramp and lip, the lip and ramp configured to produce a first oblique shock that extends outwardly from a forward portion of the ramp to pass ahead of the lip, and a terminal shock that extends outwardly from a rearward portion of the ramp to one of the followingxo) a region just ahead of the lipx1) substantially to said lip.A non-uniform shock system is created that generates a central region of nearly isentropic compression and relatively ram recovery and an outer region of reduced ram recovery but entailing reduced cowl angle and drag. Translating cowl structure and also nozzle integration with the fuselage contour to reduce boat tail drag are also provided.


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    Supersonic aircraft jet engine installation


    Beteiligte:

    Erscheinungsdatum :

    10.03.2022


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



    Supersonic aircraft jet engine installation

    HENNE PRESTON A / CONNERS TIMOTHY R / HOWE DONALD C | Europäisches Patentamt | 2016

    Freier Zugriff

    SUPERSONIC AIRCRAFT PROPULSION INSTALLATION

    BRADBROOK STEPHEN J | Europäisches Patentamt | 2020

    Freier Zugriff

    Supersonic aircraft propulsion installation

    Europäisches Patentamt | 2018

    Freier Zugriff

    Supersonic aircraft propulsion installation

    BRADBROOK STEPHEN J | Europäisches Patentamt | 2022

    Freier Zugriff

    SUPERSONIC AIRCRAFT JET ENGINE

    CHASE JAMES D / GARZON GERMAN ANDRES | Europäisches Patentamt | 2016

    Freier Zugriff