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.
Theoretical performance of hydrogen-oxygen rocket thrust chambers
NASA -- Tech Report
1961
82 pages
Report
English
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Cooling of rocket thrust chambers with liquid oxygen
NTRS | 1990
|Cooling of rocket thrust chambers with liquid oxygen
AIAA | 1990
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