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.
Theoretical performance of liquid Hydrogen with liquid Oxygen as rocket propellant
NASA -- Memo
National Aeronautics and Space Administration -- Memorandums ; Memo n 5-21-59E
1959
139 pages
Report
Englisch
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