Pylon cross-sectional geometries that are intended to reduce propulsion system installation drag were investigated on a 1/17th-scale low-wing transport model in the NASA Langley 16-Foot Transonic Tunnel. The basic design philosophy for these pylons was to alleviate flow acceleration without introducing severe adverse pressure gradients near the pylon/wing junction. This was achieved by means of a gradually, diverging pylon with maximum thickness occurring at the wing trailing edge. The pylon closure occurs aft of the wing trailing edge. The force, surface pressure and surface flow visualization data obtained support this concept.


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    Title :

    Experimental study of pylon geometries for transport aircraft



    Publication date :

    1992-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




    Experimental study of pylon geometries for transport aircraft

    NAIK, DINESH / INGRALDI, ANTHONY / PENDERGRAFT, JR., ODIS | AIAA | 1992


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