The results of a wind tunnel investigation on an all flush orifice air data system for use on a KC-135A aircraft are presented. The investigation was performed to determine the applicability of fixed all flush orifice air data systems that use only aircraft surfaces for orifices on the nose of the model (in a configuration similar to that of the shuttle entry air data system) provided the measurements required for the determination of stagnation pressure, angle of attack, and angle of sideslip. For the measurement of static pressure, additional flush orifices in positions on the sides of the fuselage corresponding to those in a standard pitot-static system were required. An acceptable but less accurate system, consisting of orifices only on the nose of the model, is defined and discussed.


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    Titel :

    Wind Tunnel Investigation of an All Flush Orifice Air Data System for a Large Subsonic Aircraft


    Beteiligte:
    T. J. Larson (Autor:in) / S. G. Flechner (Autor:in) / P. M. Siemers (Autor:in)

    Erscheinungsdatum :

    1980


    Format / Umfang :

    98 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Wind tunnel investigation of an all flush orifice air data system for a large subsonic aircraft

    Larson, T. J. / Flechner, S. G. / Siemers, P. M., III | NTRS | 1980


    Subsonic tests of an all-flush-pressure-orifice air data system

    Larson, T. J. / Siemers, P. M., III | NTRS | 1981



    Subsonic wind-tunnel performance

    Eckert, W. T. / Jope, J. / Mort, K. W. | NTRS | 1977


    Subsonic Wind Tunnel Facilities

    M. A. Kidd | NTIS | 1972