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
English
© Metadata Copyright Elsevier B. V. All rights reserved.
Liquid oxygen as rocket propellant
Engineering Index Backfile | 1955
|Propellant Injection in a Liquid Oxygen-Gaseous Hydrogen Rocket Engine
Online Contents | 1996
|