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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    Title :

    Transonic wall interference effects on bodies of revolution.


    Contributors:

    Conference:

    American Institute of Aeronautics and Astronautics, Aerodynamic Testing Conference


    Publication date :

    1972-09-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English






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