Wind tunnel tests were conducted at Mach 0.9 to 1.4; design Mach numbers of nozzles were 2.0 and 2.5 and number of clustered nozzles ranged from 2 to 6; some models were tested with configurations of extended, shrouded, flush, and canted nozzles, results obtained.


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    Titel :

    Investigation of net-thrust and base-pressure characteristics of cylindrical afterbodies with clustered supersonic nozzles at transonic Mach numbers


    Weitere Titelangaben:

    NASA -- Tech Notes


    Beteiligte:


    Erscheinungsdatum :

    1961


    Format / Umfang :

    46 pages


    Medientyp :

    Report


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :