Experimental combustion efficiencies of 11 different propellant combinations were determined in nominal 200 lb thrust rocket engine at three chamber lengths and compared with analytical results; data agreed with predicted results except for hydrazine, which may have decomposed in liquid phase, and ammonia-fluorine.


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    Titel :

    Propellant vaporization as criterion for rocket-engine design -- Experimental performance, vaporization, and heat-transfer rates with various propellant combinations


    Weitere Titelangaben:

    NASA -- Memo


    Beteiligte:
    Clark, B.J. (Autor:in) / Hersch, M. (Autor:in) / Priem, R.J. (Autor:in)


    Erscheinungsdatum :

    1959


    Format / Umfang :

    31 pages


    Medientyp :

    Report


    Format :

    Print


    Sprache :

    Englisch