The objective of the current work is to experimentally characterize the flowfield associated with an uni-element shear coaxial injector burning liquid oxygen/gaseous hydrogen (LOX/GH2) propellants. These experiments were carried out in an optically-accessible rocket chamber operating at a high pressure (approximately 400 psia). Quantitative measurements of drop size and velocity were obtained along with qualitative measurements of the disintegrating jet.


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    Titel :

    Flowfield Characterization in a LOX/GH2 Propellant Rocket


    Beteiligte:
    Pal, S. (Autor:in) / Moser, M. D. (Autor:in) / Ryan, H. M. (Autor:in) / Foust, M. J. (Autor:in) / Santoro, R. J. (Autor:in)


    Erscheinungsdatum :

    01.07.1993


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch




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