Uncooled rocket engine was investigated over chamber pressure from 45 to 300 psia and oxidant-fuel ratio from 2 to 7; combustion dead times were calculated from chamber-pressure frequency measurements; dead time decreased with increased chamber pressure at constant oxidant-fuel ratio or liquid-oxygen injection velocity; close agreement obtained between measured dead times and those calculated from frequency measurements.


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    Title :

    Relations of combustion dead time to engine variables for 20,000-pound-thrust gaseous-hydrogen-liquid-oxygen rocket engine


    Additional title:

    NASA -- Tech Note


    Contributors:


    Publication date :

    1961


    Size :

    23 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :