A model is presented for longitudinal shock-wave propagation in liquid propellant rocket engines. The equations, which include the effects of gaseous dissociation, contain appropriate terms to account for the drag, possible shattering, evaporation, and subsequent combustion of the liquid fuel drops. The equations are solved numerically on a digital computer. A comparison of the results obtained with previous experimental work performed in a shock tube indicates good agreement for shock-wave pressure ratios above about 3.5. (Author)


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    Title :

    Shock-Wave Propagation in Liquid Propellant Rocket Engines


    Contributors:
    V. D. Agosta (author) / W. Chinitz (author)

    Publication date :

    1961


    Size :

    2 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English