The dynamics of unsteady vortex flow around the wing in the hydrodynamic tunnel was investigated. The hypothesis of cross-sensitivity detachable small vortex excitation flow velocity in the region of leading edge with nasal influx was confirmed.


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    Title :

    Unsteady flow around airfoil at large angles of attack


    Contributors:


    Publication date :

    2013-10-01


    Size :

    808328 byte




    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English



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