Data for liquid hydrogen, liquid oxygen thrust chambers at chamber pressures from 15 to 1200 psia, area ratios to 300, and percent fuel from about 8 to 34 for equilibrium and frozen composition during expansion; specific impulse in vacuum, specific impulse, combustion chamber and nozzle-exit temperature, characistic velocity, and ratio of chamber to nozzle exit pressure included; data are presented in graphs.


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    Title :

    Theoretical performance of hydrogen-oxygen rocket thrust chambers


    Additional title:

    NASA -- Tech Report


    Contributors:


    Publication date :

    1961


    Size :

    82 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :


    Theoretical performance of hydrogen oxygen rocket thrust chambers

    Sievers, Gilbert K. ;Tomazic, William A. ;Kinney, George R. | SLUB | 1962


    Theoretical performance of hydrogen-oxygen rocket thrust chambers

    Sievers, Gilbert K. / Tomazic, William A. / Kinney, George R. | TIBKAT | 1961


    Cooling of rocket thrust chambers with liquid oxygen

    Armstrong, Elizabeth S. / Schlumberger, Julie A. | NTRS | 1990


    Cooling of rocket thrust chambers with liquid oxygen

    ARMSTRONG, ELIZABETH / SCHLUMBERGER, JULIE | AIAA | 1990