Comparison of flowfield surveys and computations of a crossing-shock wave/boundary layer interaction

T. J. Garrison, G. S. Settles, N. Narayanswamit, D. D. Knight, C. C. Horstman

Research output: Contribution to conferencePaperpeer-review

5 Scopus citations

Abstract

A joint experimental and computational study has been performed to investigate the flowfield structure created by two crossing oblique shock waves interacting with a turbulent boundary layer. Such an interaction is of practical importance in the design of high-speed sidewall-compression inlets. The interaction is created by a test model consisting of two sharp fins mounted at 15 degrees angle-of-attack to a flat plate, placed in a Mach 3.85 freestream flow. Two computational solutions, one using a Baldwin-Lomax algebraic turbulent eddy viscosity model and one using a modified K-ε (Rodi) turbulence model, are compared with experimental flowfield data obtained from a fast-response five-hole probe. Both the experiment and the computations show that the flowfield is dominated by a large, low-Mach-number, low-total-pressure separated region located on the interaction centerline. A comparison of the results shows significant differences between experiment and computations within this separated region. Outside the separated region, the experiment and computations are in good agreement. Additionally, the comparison shows that both turbulence models provide similar results, with neither model being clearly superior in predicting the flowfield.

Original languageEnglish (US)
StatePublished - Jan 1 1994
EventAIAA Fluid Dynamics Conference, 1994 - Colorado Springs, United States
Duration: Jun 20 1994Jun 23 1994

Other

OtherAIAA Fluid Dynamics Conference, 1994
CountryUnited States
CityColorado Springs
Period6/20/946/23/94

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Engineering (miscellaneous)

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