A semi-analytical calculation of combustion gas parameters and the characteristic velocity performance, based on the experimental pressure distribution of LOX/GH2 rocket combustion chambers with constant cross-sectional areas and coaxial type injectors. The thrust level was 300 kgf with a nominal chamber pressure of 20 atm. The oxidant-fuel mixture ratios ranged from approximately 2 to 10. The combustion chamber geometry varied in lengths from 11 to 26 cm and contraction ratios of 2.03, 3.41 and 4.46, with a constant nozzle throat area. The injector has twelve coaxial elements with three replaceable faceplates having different hydrogen port areas.


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    Titel :

    An Experimental-Analytical Calculation of Combustion Performance of LOX/GH2 Rocket with Coaxial Injectors


    Beteiligte:
    N. Yatsuyanagi (Autor:in) / A. Suzuki (Autor:in) / H. Gomi (Autor:in) / H. Sakamoto (Autor:in)

    Erscheinungsdatum :

    1976


    Format / Umfang :

    22 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




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