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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    Titel :

    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


    Weitere Titelangaben:

    NASA -- Tech Note


    Beteiligte:


    Erscheinungsdatum :

    1960


    Format / Umfang :

    19 pages


    Medientyp :

    Report


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :