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.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Experimental study of pylon geometries for transport aircraft


    Beteiligte:

    Erscheinungsdatum :

    1992-01-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Experimental study of pylon geometries for transport aircraft

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


    AIRCRAFT PYLON

    HERZIG YOAV | Europäisches Patentamt | 2015

    Freier Zugriff

    Aircraft pylon

    HERZIG YOAV | Europäisches Patentamt | 2022

    Freier Zugriff

    AIRCRAFT PYLON

    HERZIG YOAV / MAROM DANIEL | Europäisches Patentamt | 2018

    Freier Zugriff

    AIRCRAFT PYLON

    HERZIG YOAV / MAROM DANIEL | Europäisches Patentamt | 2018

    Freier Zugriff