Experimental investigations of mach 3 shock-wave turbulent boundary layer interactions

Patrick Bookey, Christopher Wyckham, Alexander Smits

Research output: Chapter in Book/Report/Conference proceedingConference contribution

21 Scopus citations

Abstract

Experiments were conducted to study two shock/turbulent boundary layer interactions in a Mach 2.9 flow. The interactions comprise a 24° compression corner and a 12° reflected shock interaction at Reθ = 2400. These low Reynolds number flows were chosen to coincide with DNS accessible Reynolds numbers in order to make direct comparisons. Measurements included mean flow surveys, surface pressure distributions, surface flow visualizations and Filtered Rayleigh Scattering (FRS).

Original languageEnglish (US)
Title of host publication35th AIAA Fluid Dynamics Conference and Exhibit
StatePublished - 2005
Event35th AIAA Fluid Dynamics Conference and Exhibit - Toronto, ON, Canada
Duration: Jun 6 2005Jun 9 2005

Publication series

Name35th AIAA Fluid Dynamics Conference and Exhibit

Other

Other35th AIAA Fluid Dynamics Conference and Exhibit
CountryCanada
CityToronto, ON
Period6/6/056/9/05

All Science Journal Classification (ASJC) codes

  • Engineering (miscellaneous)
  • Aerospace Engineering

Fingerprint Dive into the research topics of 'Experimental investigations of mach 3 shock-wave turbulent boundary layer interactions'. Together they form a unique fingerprint.

  • Cite this

    Bookey, P., Wyckham, C., & Smits, A. (2005). Experimental investigations of mach 3 shock-wave turbulent boundary layer interactions. In 35th AIAA Fluid Dynamics Conference and Exhibit (35th AIAA Fluid Dynamics Conference and Exhibit).