An asymmetrical hypersonic inlet cowl lip was numerically studied to explore a new approach of thermal protection. Comparative analyses of the flowfield structure and wall heat transfer with a symmetrical cowl lip were conducted. Results indicate that the peak heat transfer rate to the wall of the asymmetrical cowl lip decreases greatly when an impinging shock intersects a bow shock. Without the impinging shock, the location of the peak heat transfer rate occurs on the wall with a small radius, which does not coincide with the location of the air stagnation point; and the wall peak heat transfer rate of the asymmetrical cowl lip is higher than those of the symmetrical cowl lip, unless the flow attack angle to the wall with a large radius exceeds 12 deg.


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Influence of Hypersonic Inlet Cowl Lip on Flowfield Structure and Thermal Load


    Beteiligte:
    Weixing, Wang (Autor:in) / Rongwei, Guo (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    01.09.2014




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch





    Inlet cowl deflection limiting strut

    SAWYERS-ABBOTT NIGEL DAVID / SCHWARZ FREDERICK M | Europäisches Patentamt | 2022

    Freier Zugriff

    INLET COWL DEFLECTION LIMITING STRUT

    SAWYERS-ABBOTT NIGEL DAVID / SCHWARZ FREDERICK M | Europäisches Patentamt | 2022

    Freier Zugriff

    Inlet cowl deflection limiting strut

    SAWYERS-ABBOTT NIGEL DAVID / SCHWARZ FREDERICK M | Europäisches Patentamt | 2020

    Freier Zugriff

    Engine cowl and inlet cover

    SPARKS RICK EARL / DOBBS SHELBY T | Europäisches Patentamt | 2016

    Freier Zugriff