A wind-tunnel investigation was conducted to determine the effects of F101 DFE (derivative fighter engine) nozzle axial positioning on the afterbody-nozzle longitudinal aerodynamic characteristics of the F-14 airplane. The model was tested in the Langley 16-Foot Transonic Tunnel at Mach numbers from 0.7 to 1.25 and angles of attack from about -2 to 6 degrees. Compressed air was used to simulate nozzle exhaust flow at jet total-pressure ratios from 1 (jet off) to about 8. The results of the investigation show that for subsonic Mach numbers the intermediate cruise nozzle position of the three positions tested resulted in the lowest drag.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Effects of Installation of F101 Dfe Exhaust Nozzles on the Afterbody-Nozzle Characteristics of the F-14 Airplane


    Beteiligte:
    D. E. Reubush (Autor:in) / J. R. Carlson (Autor:in)

    Erscheinungsdatum :

    1982


    Format / Umfang :

    133 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch