Theoretical performance for both equilibrium and frozen composition during expansion was calculated at chamber pressures of 60, 150, 300, and 600 psi abs and wide range of pressure and oxidant-fuel ratios; data given to estimate performance parameters at chamber pressures other than those for which data are tabulated.


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    Titel :

    Theoretical performance of liquid Hydrogen with liquid Oxygen as rocket propellant


    Weitere Titelangaben:

    NASA -- Memo


    Beteiligte:
    Gordon, S. (Autor:in) / McBride, B.J. (Autor:in)


    Erscheinungsdatum :

    1959


    Format / Umfang :

    139 pages


    Medientyp :

    Report


    Format :

    Print


    Sprache :

    Englisch






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