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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    Title :

    Theoretical performance of liquid Hydrogen with liquid Oxygen as rocket propellant


    Additional title:

    NASA -- Memo


    Contributors:
    Gordon, S. (author) / McBride, B.J. (author)


    Publication date :

    1959


    Size :

    139 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English