Turbulence measurements with PIV in a hypersonic shock boundary layer interaction

Anne Marie Schreyer, Dipankar Sahoo, Alexander J. Smits

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

4 Scopus citations


Experiments were performed to study a hypersonic shock/turbulent boundary layer interaction. The Mach number was 7.2, the shock wave was generated by a 33° compression corner, and the Reynolds number based on momentum thickness of the incoming boundary layer was Reθ = 3500. A separation bubble developed at the compression corner. The measurements were performed with Particle Image Velocimetry (PIV) and included mean flow surveys as well as turbulence measurements. Data were taken throughout the separated flow, downstream of reattachment, and through a subsequent expansion formed by a matching 33° deflection corner. The wall normal velocity fluctuations and Reynolds shear stresses showed strong amplification under the influence of the shock wave. Also in the expansion further downstream, the streamwise and wall normal velocity fluctuations, and the Reynolds stresses were further amplified.

Original languageEnglish (US)
Title of host publication41st AIAA Fluid Dynamics Conference and Exhibit
StatePublished - Dec 1 2011
Event41st AIAA Fluid Dynamics Conference and Exhibit 2011 - Honolulu, HI, United States
Duration: Jun 27 2011Jun 30 2011


Other41st AIAA Fluid Dynamics Conference and Exhibit 2011
Country/TerritoryUnited States
CityHonolulu, HI

All Science Journal Classification (ASJC) codes

  • Fluid Flow and Transfer Processes
  • Energy Engineering and Power Technology
  • Aerospace Engineering
  • Mechanical Engineering


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