An experimental investigation to determine the effects of various empennage parameters on aft-end drag and tail interference drag characteristics of a twin-engine, axisymmetric nozzle, afterbody model has been conducted in the Langley 16-Foot Transonic Tunnel. Model variables included: horizontal tail location; vertical tail location, toe angle, cant angle, configuration (single and twin) and airfoil (Symmetrical and cambered); and tail booms. Tests were conducted over a Mach number range from 0.6 to 1.2 and over an angle-of-attack range from -2 to 10 deg. Nozzle pressure ratio was varied from jet off to approximately 10.0.


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    Title :

    Effects of various empennage parameters on the aerodynamic characteristics of a twin-engine afterbody model


    Contributors:

    Conference:

    American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting ; 1983 ; Reno, NV


    Publication date :

    1983-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :