Interaction between a conical shock wave and a plane compressible turbulent boundary layer at Mach 2.05

Hale, Jason

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https://hdl.handle.net/2142/72992 Copy

Description

Title

Interaction between a conical shock wave and a plane compressible turbulent boundary layer at Mach 2.05

Author(s)

Hale, Jason

Issue Date

2015-01-21

Director of Research (if dissertation) or Advisor (if thesis)

• Elliott, Gregory S.
• Dutton, J.C.

Department of Study

Aerospace Engineering

Discipline

Aerospace Engineering

Degree Granting Institution

University of Illinois at Urbana-Champaign

Degree Name

M.S.

Degree Level

Thesis

Keyword(s)

• Taylor Maccoll
• Cone Flow
• Shock Boundary Layer Interaction (SBLI)
• Shock Wave Boundary Layer Interaction
• Pressure Sensitive Paint
• Particle Image Velocimetry
• Supersonic

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.

Graduation Semester

2014-12

Permalink

http://hdl.handle.net/2142/72992

Copyright and License Information

Copyright 2014 Jason Hale

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