An experimental investigation was conducted in the Langley 16-Foot Transonic Tunnel at free-stream Mach numbers from 0.70 to 0.82 and angles of attack from -2.5 to 4.0 degrees to determine the integration effects of pylon-mounted underwing forward and rearward separate-flow, flow-through nacelles on a high-wing transonic transport configuration. The results showed that the installed drag of the nacelle/pylon in the rearward location was slightly less than that of the nacelle/pylon in the forward location. This reduction was due to the reduction in calculated skin friction of the nacelle/pylon configuration. In all cases the combined value of form, wave, and interference drag was excessively high. However, the configuration with the nacelle/pylon in a rearward location produced an increase in lift over that of the basic wing-body configuration.


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    Title :

    Integration Effects of Underwing Forward- and Rearward-Mounted Separate-Flow, Flow-Through Nacelles on a High-Wing Transport


    Contributors:
    M. Lamb (author) / W. K. Abeyounis (author)

    Publication date :

    1986


    Size :

    31 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English