Unsteady aerodynamic loads were measured on an oscillating NACA 64A010 airfoil In the NASA Ames 11 by 11 ft Transonic Wind Tunnel. Data are presented to show the effect of the unsteady shock-wave/boundary-layer interaction on the fundamental frequency lift, moment, and pressure distributions. The data show that weak shock waves induce an unsteady pressure distribution that can be predicted quite well, while stronger shock waves cause complex frequency-dependent distributions due to flow separation. An experimental test of the principles of linearity and superposition showed that they hold for weak shock waves while flows with stronger shock waves cannot be superimposed.


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    Titel :

    Transonic Shock-Wave/Boundary-Layer Interactions on an Oscillating Airfoil


    Beteiligte:

    Kongress:

    Structures, Structural Dynamics, and Materials ; 1979 ; Saint Louis, MO, United States


    Erschienen in:

    AIAA Journal ; 18 , 11


    Erscheinungsdatum :

    1980-11-01


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Transonic Shock-Wave/Boundary-Layer Interactions on an Oscillating Airfoil

    Sanford S. Davis / Gerald N. Malcolm | AIAA | 1980



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    Shock wave-boundary layer interactions in laminar transonic flow.

    Brilliant, H. M. / Adamson, T. C., Jr. | NTRS | 1973