Abstract When integrated with supersonic/hypersonic flight vehicles the ramp shock/boundary layer interaction occurs in streamline-traced inward-turning inlets exhibit complex three-dimensional characteristic. Two simplified flow models named the single-sided model and the double-sided model were abstracted to investigate the flow phenomenon in this paper. The single-sided model was designed to focus on curved ramp shock/boundary layer interaction near the corner of the inlet while the double-sided model aimed to expose the coupling mechanism and the evolution process near the symmetry plane of the inlet. The separation region of the single-sided model was observed to develop along the leading edge of the three-dimensional compression ramp using oil flow visualisation. It started at the junction of the ramp and the sidewall, spanned the whole test model, and appeared as a ‘scimitar’ shape with a maximum streamwise length of 0.58. On the other hand, a symmetry separation pattern was observed in the double-sided model. The separation region was ‘crescent-shaped’, originated from the junctions of the ramp and two sidewalls, and coalesced at the symmetry plane, inducing a maximum streamwise separation scale of 0.78 on the symmetry plane. The measured surface pressure distributions showed that the shock wave/boundary layer interactions in the two models behaved similarly around the ramp-sidewall junction.
Experimental and numerical investigation of shock wave/boundary layer interactions induced by curved back-swept compression ramp
2023-09-14
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Unsteadiness in Swept-Compression-Ramp Shock/Turbulent-Boundary-Layer Interactions (AIAA 2017-0987)
British Library Conference Proceedings | 2017
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