Wind tunnel investigation to determine effect on thrust for nozzle overexpansion of cylindrical afterbody with single nozzle such as used in rocket engines was conducted at Mach numbers from 0.9 to 1. 4; results indicated that proper balance between nozzle overexpansion and base area exists, which will produce maximum afterbody net thrust factor over given operating range.


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    Title :

    Effect on thrust minus base drag of exchanging base area for nozzle expansion in supersonic nozzles at transonic Mach numbers


    Additional title:

    NASA -- Tech Note


    Contributors:


    Publication date :

    1961


    Size :

    30 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :