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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    Titel :

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


    Weitere Titelangaben:

    NASA -- Tech Note


    Beteiligte:
    Scott, W.R. (Autor:in)


    Erscheinungsdatum :

    1961


    Format / Umfang :

    48 pages


    Medientyp :

    Report


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :



    Optimizing Exhaust — Nozzle/Airframe Thrust Minus Drag

    Migdal, David / Greathouse, William K. | SAE Technical Papers | 1968


    Optimizing exhaust -- Nozzle/airframe thrust minus drag

    Migdal, D. / Greathouse, W.K. | Engineering Index Backfile | 1968



    Ejector/Engine/Nacelle Integration for Increased Thrust Minus Drag

    Khalid, Syed / Sokhey, Jack / Chakka, Pitchaiah et al. | AIAA | 2010