Abstract
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 language | English (US) |
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Title of host publication | 41st AIAA Fluid Dynamics Conference and Exhibit |
State | Published - Dec 1 2011 |
Event | 41st AIAA Fluid Dynamics Conference and Exhibit 2011 - Honolulu, HI, United States Duration: Jun 27 2011 → Jun 30 2011 |
Other
Other | 41st AIAA Fluid Dynamics Conference and Exhibit 2011 |
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Country/Territory | United States |
City | Honolulu, HI |
Period | 6/27/11 → 6/30/11 |
All Science Journal Classification (ASJC) codes
- Fluid Flow and Transfer Processes
- Energy Engineering and Power Technology
- Aerospace Engineering
- Mechanical Engineering