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Some new aspects of the shock-wave/boundary-layer interaction in compression-ramp flows

Published online by Cambridge University Press:  21 April 2006

J. Andreopoulos  and
K. C. Muck
J. Andreopoulos
Affiliation:
Gas Dynamics Laboratory, Mechanical and Aerospace Engineering Department, Princeton University, Princeton, NJ 08544, USA Present address: Department of Mechanical Engineering, City College of the City University of New York, New York, NY 10031, USA.
K. C. Muck
Affiliation:
Gas Dynamics Laboratory, Mechanical and Aerospace Engineering Department, Princeton University, Princeton, NJ 08544, USA Present address: Department of Mechanical Engineering, University of Maryland. Mail Stop: Center for Fire Research, National Bureau of Standards, Gaithersburg, MD 20899, USA.
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Abstract

The present study of the pressure fluctuations in the interaction region oif a two-dimensionals compression flow established that the frequency of the shock-wave unsteadiness is of the same order as the bursting frequency of the upstream boundary layer and that this frequency is independent of the downstream separated flow. The conditional-sampling technique developed herein is capable of separating phenomena due to shock-wave oscillations from those due to transport phenomena of turbulence. The results show that turbulence as inferred from wall-pressure fluctuations may be significantly amplified approaching the shock.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 180 , July 1987 , pp. 405 - 428
Copyright
© 1987 Cambridge University Press

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References

Andreopoulos, J., Durst, F., Zaric, Z. & Jovanovic, J. 1984 Influence of Reynolds number on characteristics of turbulent wall boundary layers. Expts Fluids 2, 7.Google Scholar
Blackwelder, R. F. & Kaplan, R. E. 1976 On the structure of the turbulent layer. J. Fluid Mech. 70, 89.Google Scholar
Bogdonoff, S. M. 1955 Some experimental studies of the separation of supersonic turbulent boundary layers. Dept. of Aeronautical Engineering, Princeton University, Princeton, NJ, Rep. 336.Google Scholar
Brown, G. L. & Thomas, S. W. 1977 Large structure in a boundary layer. Phys. Fluids 20, S242.Google Scholar
Coe, C. F. 1969 Surface-pressure fluctuations associated with aerodynamic noise. NASA SP-207, p. 409.
Dolling, D. S. & Murphy, M. 1982 Wall pressure fluctuations in a supersonic separated compression ramp flowfield. AIAA Paper 82-0986.
Dolling, D. S. & Or, C. T. 1983 Unsteadiness of the shock wave structure in attached and separated compression ramp flow fields. AIAA Paper 83-1715.
Dussauge, J. P., Muck, K. C. & Andreopoulos, J. 1985 Properties of wall pressure fluctuations in a separated flow over a compression ramp. IUTAM Symposium on Turbulent Shear Layer/Shock Wave Interactions, Palaiseau, France (ed. J. Délery), pp. 383–392. Springer.
Eckelmann, H. 1979 The structure of the viscous sublayer and the adjacent wall region in a turbulent channel flow. J. Fluid Mech. 65, 433.Google Scholar
Haverbeke, A., Wood, D. H. & Smits, A. J. 1979 Uncertainties and errors in conditional sampling. 2nd Turbulent Shear flow Symp., Imperial College.
Kaufman, L. G., Korkegi, R. H. & Morton, L. 1972 Shock impingement caused by boundary layer separation ahead of blunt fins. Aeronautical Research Laboratories 72–0118.
Kim, H. T., Kline, S. J. & Reynolds, W. C. 1971 The production of turbulence near a smooth wall in a turbulent boundary layer. J. Fluid Mech. 50, 133.Google Scholar
Kim, J. & Moin, P. 1986 The structure of the vorticity field in turbulent channel flow. Part 2. Study of ensemble-average fields. J. Fluid Mech. 162, 339.Google Scholar
Kistler, A. L. 1964 Fluctuating wall pressure under a separated supersonic flow. J. Acoust. Soc. Am. 36, 543.Google Scholar
Kiya, M. & Sasaki, K. 1985 Turbulence structure and unsteadiness in a separation-reattachment flow. 5th Turbulent Shear Flow Symp., Cornell University.
Muck, K. C., Dussauge, J. P. & Bogdonoff, S. M. 1985 Structure of the wall pressure fluctuations in a shock-induced separated turbulent flow. AIAA Paper 85-0179.
Murlis, J., Tsai, H. M. & Bradshaw, P. 1982 The structure of turbulent boundary layers at low Reynolds numbers. J. Fluid Mech. 122, 13.Google Scholar
Owen, F. K., Horstmann, C. C. & Kussoy, M. I. 1975 Mean and fluctuating flow measurements of a fully-developed non-adiabatic hypersonic boundary layer. J. Fluid Mech. 70, 292.Google Scholar
Plotkin, K. J. 1975 Shock wave oscillation drive by turbulent boundary layer fluctuations. AIAA J. 1036.
Price, A. E. & Stalling, R. L. 1967 Investigation of turbulent separated flows in the vicinity of fin type protuberances at supersonic Mach numbers. NASA TN D-3840.
Settles, G. S. 1975 An experimental study of compressible turbulent boundary layer separation at high Reynolds numbers. Ph.D. dissertation, Aerospace and Mechanical Sciences Department, Princeton University, Princeton, NJ.
Settles, G. S., Fitzpatrick, T. J. & Bogdonoff, S. M. 1979 Detailed study of attached and separated compression corner flowfields in high Reynolds number supersonic flow. AIAA J. 17, 579.Google Scholar
Spina, E. F. & Smits, A. J. 1986 Organized structure in a supersonic turbulent boundary layer. Princeton University Rep. MAE-1736.Google Scholar
Thomas, A. S. W. & Bull, M. K. 1983 On the role of wall-pressure fluctuations in deterministic motions in the turbulent boundary layer. J. Fluid Mech. 128, 283.Google Scholar
Willmarth, W. & Sharma, L. K. 1984 Study of turbulent structure with hot-wires smaller than the viscous length. J. Fluid Mech. 142, 121.Google Scholar
Winkelmann, A. E. 1972 Experimental investigations of a fin protuberance partially immersed in a turbulent boundary layer at Mach 5. NOLTR-72-33.