During transient start-up and shutdown of rocket engines under sea-level conditions, the flow inside the supersonic part of the nozzle separates from the wall. The separated flow is asymmetrically distributed around the circumference and hence induces side loads. A cold flow subscale test campaign was carried out at DLR to study a device that reduces the side loads of a thrust-optimized parabolic nozzle under transient conditions. A detailed parametrical study was performed. The experimental data demonstrated and quantified the side load reduction potential of the device.


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Optimization of a Rocket Nozzle Side Load Reduction Device


    Beteiligte:
    Stark, R. (Autor:in) / Génin, C. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    2016-06-30


    Format / Umfang :

    8 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch






    Optimisation of a Rocket Nozzle Side Load Reduction Device

    Stark, Ralf / Genin, Chloe | AIAA | 2012



    Experimental Study on Rocket Nozzle Side Load Reduction

    Stark, Ralf / Génin, Chloé | AIAA | 2011