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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    Titel :

    Unsteady flow around airfoil at large angles of attack


    Beteiligte:
    Udartsev, E. P. (Autor:in) / Shvets, O. V. (Autor:in) / Pereverzev, O. M. (Autor:in) / Alekseenko, S. I. (Autor:in)


    Erscheinungsdatum :

    2013-10-01


    Format / Umfang :

    808328 byte




    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch



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