Efforts to develop a near sonic transport have placed renewed emphasis on obtaining accurate aerodynamic force and pressure data in the near sonic speed range. Comparison of wind-tunnel and flight data obtained for a blunt-nose body of revolution showed significant discrepancies in drag levels near Mach 1 - apparently due to wind-tunnel wall interference. Subsequent tests of geometrically similar bodies of revolution showed that increasing the model-to-test-section blockage ratio from 0.00017 to 0.0043 resulted in altered drag curve shapes, delayed drag divergence, and 'transonic creep' from subsonic drag levels due to increased wall interference.


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    Titel :

    Transonic wall interference effects on bodies of revolution.


    Beteiligte:
    Couch, L. M. (Autor:in)

    Kongress:

    American Institute of Aeronautics and Astronautics, Aerodynamic Testing Conference


    Erscheinungsdatum :

    01.09.1972


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch






    Calculation of transonic wall interference

    DONEGAN, T. / BENEK, J. / ERICKSON, JR., J. | AIAA | 1987