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.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Theoretical performance of hydrogen-oxygen rocket thrust chambers


    Weitere Titelangaben:

    NASA -- Tech Report


    Beteiligte:
    Sievers, G.K. (Autor:in) / Tomazic, W.A. (Autor:in) / Kinney, G.R. (Autor:in)


    Erscheinungsdatum :

    1961


    Format / Umfang :

    82 pages


    Medientyp :

    Report


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :


    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