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 . The lower-lip flow is characterized by a rapid acceleration around the leading edge and an 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.
Normal-Shock/Boundary-Layer Interactions in Transonic Intakes at High Incidence
AIAA Journal ; 57 , 7 ; 2867-2880
2019-03-28
14 pages
Article (Journal)
Electronic Resource
English
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