The effect of three-dimensional, longitudinal contouring of jet engine nozzle afterbodies is investigated experimentally in a water tunnel facility. Both laminar and turbulent Reynolds numbers are tested for three different afterbody configurations. Results indicate that forced mixer lobe technology can be applied to nozzle afterbodies and decrease drag coefficient by as much as 70 percent. Improved exhaust mixing is also possible through such contouring. Exhaust gas attenuation benefits of 125 percent have been recorded.


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    Titel :

    Lobed nozzle afterbody research


    Beteiligte:

    Erscheinungsdatum :

    01.06.1987


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Lobed nozzle afterbody research

    Russell, W.D. | Tema Archiv | 1987



    F-15 Nozzle/Afterbody Integration

    Richard E. Martens | AIAA | 1976


    F-15 nozzle/afterbody integration

    MARTENS, R. | AIAA | 1974