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.


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    Title :

    Propellant vaporization as criterion for rocket-engine design: experimental effect of chamber diameter on liquid Oxygen-Heptane performance


    Additional title:

    NASA -- Tech Note


    Contributors:


    Publication date :

    1959


    Size :

    22 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English