Study is based on hypothesis that propellant vaporization is controlling factor in rocket engine combustion; effect of combustor gas velocity on performance of pair of impinging heptane jets reacting in highly atomized oxygen atmosphere is evaluated in nominal 200-lb thrust combustor; analysis of results.
Propellant vaporization as criterion for rocket-engine design: experimental effect of chamber diameter on liquid Oxygen-Heptane performance
NASA -- Tech Note
1959
22 pages
Article (Journal)
English
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