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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    Title :

    Flowfield Characterization in a LOX/GH2 Propellant Rocket


    Contributors:
    S. Pal (author) / M. D. Moser (author) / H. M. Ryan (author) / M. J. Foust (author) / R. J. Santoro (author)

    Publication date :

    1993


    Size :

    31 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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