TY - JOUR
T1 - Experimental study of a Mach 3 compression ramp interaction at re θ = 2400
AU - Ringuette, Matthew J.
AU - Bookey, Patrick
AU - Wyckham, Christopher
AU - Smits, Alexander J.
N1 - Funding Information:
We would like to acknowledge the support from the U.S. Air Force Office of Scientific Research under grant no. FA 9550-06-1-0323. We would also like to thank Noel Clemens, Pablo Bueno, and Frank Wise of the University of Texas at Austin, Glenn Atkinson of the Princeton University Physics Department machine shop, and Christina Peabody for their help with the design of the Kulite transducer holder and supporting electronics. We are grateful for the help of William Stokes on the experimental setup and running the tunnel, Zhilei Wu for assistance in operating the facility, and Pino Martín for allowing us access to her direct numerical simulation database.
PY - 2009/2
Y1 - 2009/2
N2 - Experiments were performed to investigate the flow in a Mach 2.9 shock wave turbulent boundary-layer interaction at a Reynolds number based on momentum thickness of 2400. The flow configuration was a nominally two-dimensional 24 deg compression ramp, which exhibited a separation bubble in the corner region. Mean flow quantities, including the velocity profile upstream and downstream of the corner, and the wall pressure through the interaction were measured. Filtered Ray leigh scattering was used to visualize the flow structure in the interaction and provide quantitative measurements of the turbulent structure angle and the intermittency of the boundary-layer edge turbulence. The shock motion was characterized by measuring the fluctuating wall pressure. The results indicate that, compared to previous measurements obtained at higher Reynolds numbers of 60-80,000, the separation bubble is approximately twice as long, the root mean square of the wall-pressure fluctuations has a relatively smaller peak, and the intermittency of the wall-pressure signal in the shock-foot region is attenuated. As in the high-Reynolds-number case, the shock motion has a broadband frequency distribution with a peak slightly below 1 kHz. The mean flow quantities, root mean square wall-pressure-fluctuation profile, wall-pressure signal, and shock-motion frequency agree well with the direct numerical simulation of a previous study at matching conditions.
AB - Experiments were performed to investigate the flow in a Mach 2.9 shock wave turbulent boundary-layer interaction at a Reynolds number based on momentum thickness of 2400. The flow configuration was a nominally two-dimensional 24 deg compression ramp, which exhibited a separation bubble in the corner region. Mean flow quantities, including the velocity profile upstream and downstream of the corner, and the wall pressure through the interaction were measured. Filtered Ray leigh scattering was used to visualize the flow structure in the interaction and provide quantitative measurements of the turbulent structure angle and the intermittency of the boundary-layer edge turbulence. The shock motion was characterized by measuring the fluctuating wall pressure. The results indicate that, compared to previous measurements obtained at higher Reynolds numbers of 60-80,000, the separation bubble is approximately twice as long, the root mean square of the wall-pressure fluctuations has a relatively smaller peak, and the intermittency of the wall-pressure signal in the shock-foot region is attenuated. As in the high-Reynolds-number case, the shock motion has a broadband frequency distribution with a peak slightly below 1 kHz. The mean flow quantities, root mean square wall-pressure-fluctuation profile, wall-pressure signal, and shock-motion frequency agree well with the direct numerical simulation of a previous study at matching conditions.
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U2 - 10.2514/1.38248
DO - 10.2514/1.38248
M3 - Article
AN - SCOPUS:60049086517
SN - 0001-1452
VL - 47
SP - 373
EP - 385
JO - AIAA journal
JF - AIAA journal
IS - 2
ER -