Data obtained in study show that canting outward of propulsive nozzles on twin-nozzle booster rocket configuration was effective in reducing base drag over range of nozzle pressure ratios at supersonic speeds; reduction in drag was greatest near design pressure ratio of nozzle.


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    Title :

    Measured base pressures on several twin rocket-nozzle configurations at mach numbers of 0.6 to 1.4 with effects due to nozzle canting and stabilizing fins


    Additional title:

    NASA -- Tech Note


    Contributors:


    Publication date :

    1960


    Size :

    19 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :