The Langley 16-foot transonic tunnel was used to determine the effects of several empennage and afterbody parameters on twin-engine aft-end aerodynamic characteristics. Model variables included twin-vertical-tail cant angle, toe angle, airfoil camber, and root-chord length and afterbody/engine interfairing shape. Tests were conducted over a Mach number range from 0.6 to 1.2 and over an angle-of-attack range from 2 deg to 10 deg. Nozzle pressure ratio was varied from 1.0 (jet off) to approximately 10.0.


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    Titel :

    Effects of twin-vertical-tail parameters on twin-engine afterbody/nozzle aerodynamic characteristics


    Beteiligte:
    Leavitt, L. D. (Autor:in) / Bare, E. A. (Autor:in)

    Erscheinungsdatum :

    1983-05-01


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :