Direct numerical simulations of shock-wave/boundary-layer interactions are performed at Mach number M = 1.7 to investigate the influence of the state of the incoming boundary layer on the interaction properties. Four shock-wave/boundary-layer interaction cases are considered, corresponding to transitional and turbulent interactions for two different shock strengths, corresponding to flow-deflection angles ϕ = 3    deg and ϕ = 6    deg . It is found that significant separation is not evident in the mean flow of any interaction; the boundary layer remains attached at ϕ = 3    deg and close to incipient separation at ϕ = 6    deg , independent of the state of the incoming boundary layer. The extent of the interaction is larger for the transitional flow cases, characterized by a wider spreading of the wall pressure rise and a slower boundary-layer recovery. The scaling analysis for the interaction length scale L developed by Souverein et al. (“A Scaling Analysis for Turbulent Shock-Wave/Boundary-Layer Interactions,” Journal of Fluid Mechanics, Vol. 714, January 2013, pp. 505–535) for turbulent interactions is found to be equally applicable for the transitional interactions. The wall-pressure spectra show that the dominant frequency range is that associated with the most energetic structures of the incoming boundary layer, and no evidence of low-frequency shock unsteadiness is noticed.


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    Titel :

    Numerical Investigation of Transitional Shock-Wave/Boundary-Layer Interaction in Supersonic Regime


    Beteiligte:

    Erschienen in:

    AIAA Journal ; 56 , 7 ; 2712-2724


    Erscheinungsdatum :

    01.07.2018




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




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