During high-incidence maneuvers, shock-wave/boundary-layer interactions can develop over transonic inlet lower lips, significantly impacting aerodynamic performance. Here, a novel experimental rig is used to investigate the nature and severity of these interactions for a typical high-incidence scenario. Furthermore, the sensitivity to changes in angle of incidence and mass-flow rate is explored, as potentially experienced across off-design operations. The reference flowfield, informed by typical climb conditions, is defined by an incidence of 23 deg and a freestream Mach number M = 0.435 . The lower-lip flow is characterized by a rapid acceleration around the leading edge and an M 1.4 shock ahead of the intake diffuser. Overall, this flowfield is found to be relatively benign, with minimal shock-induced separation. Downstream of the interaction, the boundary layer recovers a healthy profile ahead of the nominal fan location. Increasing the incidence by 2 deg, the separation becomes noticeably larger and unsteadiness develops. Detrimental effects are exacerbated at an even higher incidence of 26 deg. Increasing the mass-flow rate over the lip by up to 15% of the initial value has minor effects on performance and is not found to inhibit the boundary-layer profile recovery.


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    Titel :

    Normal-Shock/Boundary-Layer Interactions in Transonic Intakes at High Incidence


    Beteiligte:
    Coschignano, A. (Autor:in) / Babinsky, H. (Autor:in) / Sheaf, C. (Autor:in) / Zamboni, G. (Autor:in)

    Erschienen in:

    AIAA Journal ; 57 , 7 ; 2867-2880


    Erscheinungsdatum :

    01.07.2019




    Medientyp :

    Aufsatz (Konferenz) , Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch





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