Three-dimensional boundary layer and wake velocity profiles were measured in flight on the supercritical wing of the F-111 transonic aircraft technology aircraft. These data, along with pressure distributions, were obtained to establish a data base with which data obtained by three-dimensional analytical techniques could be correlated. Only a brief summary of the total data base is given. The data presented represented one chord station at a wing leading-edge sweep angle of 26 deg. They cover an angle of attack range from 6 degs to 9 degs at free-stream Mach numbers from 0.85 to 0.90. A brief discussion of the techniques used to obtain the boundary layer and wake profiles is included.


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    Title :

    In-flight three-dimensional boundary layer and wake measurements from a swept supercritical wing


    Contributors:
    Lux, D. P. (author)


    Publication date :

    1978-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English





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