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Title:Interaction between a conical shock wave and a plane compressible turbulent boundary layer at Mach 2.05
Author(s):Hale, Jason
Advisor(s):Elliott, Gregory S.; Dutton, J.C.
Department / Program:Aerospace Engineering
Discipline:Aerospace Engineering
Degree Granting Institution:University of Illinois at Urbana-Champaign
Subject(s):Taylor Maccoll
Cone Flow
Shock Boundary Layer Interaction (SBLI)
Shock Wave Boundary Layer Interaction
Pressure Sensitive Paint
Particle Image Velocimetry
Abstract:The interaction between an impinging conical shock wave with a plane compressible turbulent boundary layer has been studied at Mach 2.05. Surface oil flow and pressure-sensitive paint (PSP) data were obtained beneath the oncoming boundary layer, while schlieren and particle image velocimetry (PIV) data were obtained in the streamwise/wall-normal (x-y) plane. Oil flow data suggested that the interaction causes two-dimensional (2D) separation near the centerline, and outside of this region three-dimensional (3D) separation that propagates fluid away from the centerline toward the sidewall. PSP results showed relatively constant upstream-influence length across the inviscid shock trace. PSP also revealed significant spanwise and streamwise expansion just downstream of the shock trace, unlike the qualitatively similar two-dimensional, wedge-generated oblique shock/boundary-layer interaction. Schlieren data suggested that the flow through the interaction was unseparated, and that there is significant unsteadiness in interaction position away from the centerline due to variation in the incoming boundary layer. PIV data showed the convection of large-scale vortical structures at velocities on the order of the streamwise velocity at the vortex center. These structures were smoothed out in the interaction. The PIV data moreover confirmed the downstream expansion shown by the PSP as well as a mean lack of flow separation. However, PIV suggested that there were some cases of instantaneous separation. Overall, the interaction diverts fluid away from a low pressure zone a little way downstream of the shock. Ultimately, the geometric three-dimensionality of the problem manifests as a preferred three-dimensionality of fluid transport next to the wall, unlike the qualitatively similar, 2D oblique shock-wave/boundary-layer interaction.
Issue Date:2015-01-21
Rights Information:Copyright 2014 Jason Hale
Date Available in IDEALS:2015-01-21
Date Deposited:2014-12

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