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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    Title :

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


    Additional title:

    NASA -- Tech Notes


    Contributors:


    Publication date :

    1961


    Size :

    46 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :