A combination of time-resolved particle image velocimetry and unsteady pressure measurements is used to analyze the unsteady flow over an aeroelastic supercritical BAC 3-11 transport-type wing configuration in subtransonic flow. The dynamic interaction between the shock wave and turbulent separation is the essential feature of the unsteady flow causing a distinct self-induced oscillation of both the wing structure and the flowfield. Results from wind-tunnel experiments with a variation of the freestream Mach number at Reynolds numbers sigma(107 m-1 are analyzed regarding the origin and nature of the unsteady shock wave-boundary layer interaction. Time-resolved particle image velocimetry results are presented for a flow case with a weak shock and incipient separation as well as for a case with medium shock strength and full-scale trailing-edge separation. The visualization of the flowfield, which is time-resolved regarding the shock wave oscillation, demonstrates the two-fold nature of the shock wave-boundary layer interaction, on the one hand being the origin of aerodynamic unsteadiness at marginally separated flow, on the other hand damping the fluctuation level at full-scale separation.


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    Title :

    Time-resolved particle image velocimetry of unsteady shock wave-boundary layer interaction


    Additional title:

    Zeitlich aufgelöste Teilchenabbildgeschwindigkeitsmessung der instationären Wechselwirkung zwischen Stoßwelle und Grenzschicht


    Contributors:

    Published in:

    AIAA Journal ; 49 , 1 ; 195-204


    Publication date :

    2011


    Size :

    10 Seiten, 12 Bilder, 40 Quellen



    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English





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