Structure of crossing-shock wave/turbulent boundary-layer interactions

T. J. Garrison, G. S. Settles, N. Narayanswami, D. D. Knight

Research output: Contribution to conferencePaperpeer-review

9 Scopus citations

Abstract

A detailed comparison of experimental and computational results on the flowfield structure of a Mach 4, 15 degree symmetric crossing-shock wave/turbulent boundary layer interaction is presented. Experimentally obtained Planar Laser Scattering images are compared with static pressure contours predicted by the computation, with the computational results showing good overall agreement with the experimental data. The experimental and computational results are used in a complementary manner to develop a detailed flowfield model of the crossing shock interaction. The flowfield structure is found to consist of a complex shock structure overlying a large viscous separated region. This region occupies a significant portion of the outflow duct and consists of an accumulation of low-Mach-number, low-stagnation-pressure fluid. This region may have significant implications for sidewall compression inlets.

Original languageEnglish (US)
StatePublished - 1992
EventAIAA/ASME/SAE/ASEE 28th Joint Propulsion Conference and Exhibit, 1992 - Nashville, United States
Duration: Jul 6 1992Jul 8 1992

Other

OtherAIAA/ASME/SAE/ASEE 28th Joint Propulsion Conference and Exhibit, 1992
Country/TerritoryUnited States
CityNashville
Period7/6/927/8/92

All Science Journal Classification (ASJC) codes

  • Mechanical Engineering
  • Aerospace Engineering
  • Energy Engineering and Power Technology
  • Electrical and Electronic Engineering
  • Control and Systems Engineering

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