Wind tunnel investigation was made at 0.60 to 1.40 Mach and jet total pressure ratios from 3 to 20; tested were 8° conical and 16° circular arc afterbody, and third afterbody having linear area variation with length; cylindrical afterbody was tested for comparison; extending from these bodies were 4 circular jet nozzles with design Mach number of 2.5, spaced symmetrically about body center line.


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    Title :

    Effects of boattailing and nozzle extension on thrust-minus-drag of multiple-jet configuration


    Additional title:

    NASA -- Tech Note


    Contributors:
    Scott, W.R. (author)


    Publication date :

    1961


    Size :

    48 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :



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