Effects of local and global mechanical distortions to hypervelocity boundary layers

Flaherty, William

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https://hdl.handle.net/2142/46630 Copy

Description

Title

Effects of local and global mechanical distortions to hypervelocity boundary layers

Author(s)

Flaherty, William

Issue Date

2014-01-16T17:56:47Z

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

Austin, Joanna M.

Doctoral Committee Chair(s)

Austin, Joanna M.

Committee Member(s)

• Elliott, Gregory S.
• Dutton, J. Craig
• Christensen, Kenneth T.

Department of Study

Aerospace Engineering

Discipline

Aerospace Engineering

Degree Granting Institution

University of Illinois at Urbana-Champaign

Degree Name

Ph.D.

Degree Level

Dissertation

Keyword(s)

• Hypersonic
• compressible flow
• heat transfer
• concave
• vortex
• curved surface

Abstract

The response of hypervelocity boundary layers to global mechanical distortions due to concave surface curvature is examined. Surface heat transfer, visual boundary layer thickness, and pressure sensitive paint (PSP) data are obtained for a suite of models with different concave surface geometries. Results are compared to predictions using existing approximate methods. Near the leading edge, good agreement is observed, but at larger pressure gradients, predictions diverge significantly from the experimental data. Up to a factor of five underprediction is reported in regions with greatest distortion. Curve fits to the experimental data are compared with surface equations. It is demonstrated that reasonable estimates of the laminar heat flux augmentation may be obtained as a function of the local turning angle for all model geometries, even at the conditions of greatest distortion. As a means of introducing additional local distortions, vortex generators are used to impose streamwise structures into the boundary layer. The response of the large scale vortical structures to an adverse pressure gradient is investigated. For a flat plate baseline case, heat transfer augmentation at similar levels to turbulent flow is measured. For the concave geometries, increases in heat transfer by factors up to 2.6 are measured over the laminar values, though for higher turning angle cases, a relaxation to below undisturbed values is reported at turning angles between 10 and 15 degrees. The scaling of heat transfer with turning angle that is identified for the laminar boundary layer response is found to be robust even in the presence of the imposed vortex structures. PSP measurements indicated that natural streaks form over concave models even when imposed vorticity is present. Correlations found between the heat transfer and natural streak formation are discussed and indicate possible vortex interactions.

Graduation Semester

2013-12

Permalink

http://hdl.handle.net/2142/46630

Copyright and License Information

Copyright 2013 William Flaherty

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