Hostname: page-component-7dd5485656-wlg5v Total loading time: 0 Render date: 2025-10-30T20:05:44.012Z Has data issue: false hasContentIssue false
  • English
  • Français

Experimental investigation of axisymmetric hypersonic shock-wave/turbulent-boundary-layer interactions

Published online by Cambridge University Press:  02 January 2013

N. Murray ,
R. Hillier  and
S. Williams
N. Murray
Affiliation:
Department of Aeronautics, Imperial College London, London SW7 2AZ, UK
R. Hillier*
Affiliation:
Department of Aeronautics, Imperial College London, London SW7 2AZ, UK
S. Williams
Affiliation:
Department of Aeronautics, Imperial College London, London SW7 2AZ, UK
*
†Email address for correspondence: r.hillier@imperial.ac.uk
Get access Rights & Permissions [Opens in a new window]

Abstract

This paper presents time-averaged data for high-Reynolds-number hypersonic shock-wave/boundary-layer interactions, using a body of revolution to achieve high standards of two-dimensionality. The data are collected at nominal Mach 8.9, but a calibration is included that permits weak flow gradients in the test section to be incorporated as part of the data interpretation or flow modelling. The axisymmetric turbulent test boundary layer is developed on a hollow cylinder, aligned axially with the flow. The shock-wave interaction with this boundary layer is then generated by two separate configurations. Firstly, an impinging shock-wave case, that uses a concentric cowl to radiate an axisymmetric shock system onto the test boundary layer: for this case both an attached flow and a separated flow interaction are formed. Secondly, use of a conical-flare afterbody to produce a separated flow interaction. Quantitative data are presented for surface pressures and heat transfer, supported by some schlieren visualization and surface oil flows. A restricted CFD programme is included to assist the interpretation of the experiments.

JFM classification

Compressible Flows: Compressible boundary layers Compressible Flows: Compressible Flows Compressible Flows: Shock waves

Information

Type
Papers
Information
Journal of Fluid Mechanics , Volume 714 , 10 January 2013 , pp. 152 - 189
Copyright
©2013 Cambridge University Press

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

Article purchase

Temporarily unavailable

Footnotes

‡

Present address: European Space Research & Technology Centre, ESTEC, Postbus 299, Keplerlaan 1, 2200 AG Noordwijk, The Netherlands.

§

Present address: Mercedes-Benz Grand Prix Limited, Brackley, Northants NN13 7BD, UK.

References

Babinsky, H. 1993 A study of roughness in turbulent hypersonic boundary layers. PhD thesis, Cranfield University, UK.Google Scholar
Babinsky, H. & Edwards, J. 1996 On the incipient separation of a turbulent hypersonic boundary layer. Aeronaut J. 100, 209–214.Google Scholar
Babinsky, H. & Harvey, J. K. 2011 Shock Wave–Boundary-Layer Interactions. Cambridge University Press.Google Scholar
Back, L. H. & Cuffel, R. F. 1970 Changes in heat transfer from turbulent boundary layers interacting with shock waves and expansion waves. AIAA J. 8, 1871–1873.Google Scholar
Baldwin, B. S. & Lomax, H. 1978 Thin layer approximation and algebraic model for separated turbulent flows. AIAA Paper 78-0257.Google Scholar
Bertin, J. L. & Cummings, R. M. 2006 Critical hypersonic aerothermodynamic phenomena. Annu. Rev. Fluid Mech. 38, 129–157.Google Scholar
Boyce, R. R. & Hillier, R. 2000 Shock-induced three-dimensional separation of an axisymmetric hypersonic turbulent boundary layer. AIAA Paper 2000-2226.CrossRefGoogle Scholar
Brown, J. L. 2011 Shock wave impingement on boundary layers at hypersonic speeds: computational analysis and uncertainty. AIAA Paper 2011-3143.CrossRefGoogle Scholar
Chanetz, B. & Coet, M.-C. 1993 Shock wave boundary layer interaction analyzed in the R5Ch wind tunnel. Aerosp. Res. 5, 43–56.Google Scholar
Chanetz, B., Benay, R., Bousquet, J.-M., Bur, R., Pot, T., Grasso, F. & Moss, J. 1998 Experimental and numerical study of the laminar separation in hypersonic flow. Aerosp. Sci. Technol. 2, 205–218.Google Scholar
Clauser, F. H. 1956 The turbulent boundary layer. Adv. Appl. Mech. 4, 1–51.CrossRefGoogle Scholar
Coleman, G. T. & Stollery, J. L. 1972 Heat transfer from hypersonic turbulent flow at a wedge compression corner. J. Fluid Mech. 56, 741–752.Google Scholar
Coleman, G. T. & Stollery, J. L. 1974 Incipient separation of axially symmetric hypersonic turbulent boundary layers. AIAA J. 12, 119.Google Scholar
Coles, D. E. 1962 Rand. Corp. Rep. R-403-PR.Google Scholar
Cook, W. J. & Felderman, E. J. 1966 Reduction of data from thin-film heat-transfer gauges: a concise numerical technique. AIAA J. 4, 561–562.Google Scholar
Denman, P. A. 1989 Experimental study of hypersonic boundary layers and base flows. PhD thesis, Imperial College London.Google Scholar
Dhawan, S. & Narasimha, R. 1958 Some properties of boundary layer flow during transition from laminar to turbulent motion. J. Fluid Mech. 3, 418–436.Google Scholar
van Driest, E. R. 1951 Turbulent boundary layers in compressible fluids. J. Aerosp. Sci. 3, 145–160.Google Scholar
van Driest, E. R. 1956 Problem of aerodynamic heating. Aeronaut. Engng Rev. 15, 26–41.Google Scholar
Dussauge, J.-P., Dupont, P. & Debieve, J.-F. 2006 Unsteadiness in shock wave boundary layer interactions with separation. Aerosp. Sci. Technol. 10 (2), 85–91.Google Scholar
Edney, B. 1968 Anomalous heat transfer and pressure distributions on blunt bodies at hypersonic speeds in the presence of an impinging shock wave. FFA report 115, Aeronautical Institute of Sweden.Google Scholar
Erdos, J. & Pallone, A. 1962 Shock–boundary layer interaction and flow separation. Proc. Heat Transfer Fluid Mech. Inst. 10, 239–254.Google Scholar
Fernando, E. M. & Smits, A. J. 1990 A supersonic turbulent boundary layer in an adverse pressure gradient. J. Fluid Mech. 211, 285–307.Google Scholar
Fernholz, H. H. & Finley, P. J. 1980 A critical commentary on mean flow data for two-dimensional compressible turbulent boundary layer data. AGARDograph 253.Google Scholar
Ganapathisubramani, B., Clemens, N. T. & Dolling, D. S. 2007 Effects of upstream boundary layer on the unsteadiness of shock-induced separation. J. Fluid Mech. 585, 369–394.Google Scholar
Hillier, R., Boyce, R. R., Creighton, S. A., Fiala, A., Jackson, A. P., Mallinson, S. G., Sheikh, A. H., Soltani, S. & Williams, S. 2002 Development of some hypersonic benchmark flows using CFD and experiment. Shock Waves 12, 375–384.Google Scholar
Holden, M. S. 1971 Establishment time of laminar separated flows. AIAA J. 9, 2296–2298.Google Scholar
Holden, M. S. 1984 Experimental studies of quasi-two-dimensional and three-dimensional viscous interaction regions induced by skewed-shock and swept-shock boundary layer interactions. AIAA Paper 1984-1677.Google Scholar
Holden, M. S. 1991 Studies of the mean and unsteady structure of turbulent boundary layer separation in hypersonic flow. AIAA Paper 1991-1778.Google Scholar
Holden, M. S., Havener, A. G. & Lee, C. H. 1986 Shock wave/turbulent boundary layer interaction in high-Reynolds number hypersonic flows. Calspan-University of Buffalo Research Centre, CUBRC-86681.Google Scholar
Holden, M. S., Wadhams, T. P. & Maclean, M. 2007 Experimental studies in hypersonic flows for facility and code validation. AIAA Paper 2007-1304.CrossRefGoogle Scholar
Holden, M. S. & Wadhams, T. P. 2001 Code validation studies of laminar shock-boundary layer and shock–shock interactions in hypersonic flow. Part A. Experimental measurements. AIAA Paper 2001–1031.Google Scholar
Holden, M. S. & Wadhams, T. P. 2003 A database of aerothermal measurements in hypersonic flows in ‘building block’ experiments for CFD validation. AIAA Paper 2003–1137.Google Scholar
Hopkins, E. J., Keating, S. J. & Bandettini, A. 1960 Photographic evidence of streamwise arrays of vortices in boundary-layer flow. NACA TN-D-328.Google Scholar
Ihrig, H. K. & Korst, H. H. 1963 Quasi-steady aspects of the adjustment of separated flow regions to transient external flows. AIAA J. 1, 934–937.Google Scholar
Jackson, A. P., Hillier, R. & Soltani, S. 2001 Experimental and computational study of laminar cavity flows at hypersonic speeds. J. Fluid Mech. 427, 329–358.Google Scholar
Keyes, F. G. 1952 The heat conductivity, viscosity, specific heat and Prandtl numbers for thirteen gases. Tech. Rept. No. 37, Massachusetts Institute of Technology, Project Squid.Google Scholar
Kirk, D. C. 1993 Hypersonic turbulent boundary layers. PhD thesis, London University.Google Scholar
Kontis, K. & Stollery, J. L. 1999 Incipient separation on flared bodies at hypersonic speeds. Aeronaut. J. 103, 405–414.Google Scholar
Kussoy, M. I. & Horstman, C. C. 1975 An experimental documentation of a hypersonic shock-wave turbulent boundary layer flow: with and without separation. NASA TM-X-62412.Google Scholar
Kussoy, M. I. & Horstman, C. C. 1989 Documentation of two- and three-dimensional hypersonic shock wave/turbulent boundary layer interaction flows. NASA TM-101075.Google Scholar
Kussoy, M. I. & Horstman, C. C. 1991 Documentation of two- and three-dimensional hypersonic shock wave/turbulent boundary layer interaction flows at Mach 8.2. NASA TM-103838.Google Scholar
Laderman, A. J. 1980 Adverse pressure gradient effects on supersonic boundary-layer turbulence. AIAA J. 18, 1186–1195.Google Scholar
Mallinson, S. G., Gai, S. L. & Mudford, N. R. 1997 Establishment of steady separated flow over a compression-corner in a free piston shock tunnel. Shock Waves 7, 249–253.CrossRefGoogle Scholar
Mallinson, S. G. & Hillier, R. 1998 Experimental and CFD study of hypersonic turbulent boundary layer development under a family of pressure gradients. In Proceedings of Third European Symposium on Aerothermodynamics for Space Vehicles, pp. 221–227.Google Scholar
Mallinson, S. G., Hillier, R., Jackson, A. P., Kirk, D. C., Soltani, S. & Zanchetta, M. 2000 Gun tunnel flow calibration: defining input conditions for hypersonic flow computations. Shock Waves 10, 313–322.Google Scholar
Menter, F. R. 1994 Two-equation eddy viscosity turbulence models for engineering applications. AIAA J. 32, 1598–1605.Google Scholar
Murray, N. 2007 Three-dimensional turbulent shock-wave/boundary-layer interactions in hypersonic flows. PhD thesis, University of London.Google Scholar
Navarro-Martinez, S. & Tutty, O. R. 2005 Numerical simulation of Goertler vortices in hypersonic compression ramps. Comput. Fluids 34, 225–247.CrossRefGoogle Scholar
Rom, J. 1963 Measurements of heat transfer in separated regions in a shock tube and in a shock tunnel. AIAA J. 1, 2193–2194.CrossRefGoogle Scholar
Roshko, A. & Thomke, G. J. 1966 Observations of turbulent reattachment behind an axisymmetric downstream-facing step in supersonic flow. AIAA J. 4, 975–980.Google Scholar
Roy, C. & Blottner, F. 2006 Review and assessment of turbulence models for hypersonic flows. Prog. Aerosp. Sci. 42, 469–530.Google Scholar
Schulein, E. 2006 Skin-friction and heat-flux measurements in shock/boundary-layer interaction flows. AIAA J. 44 (8), 1732–1741.CrossRefGoogle Scholar
Schulein, E., Krogmann, P. & Stanewsky, E. 1996 Documentation of two-dimensional impinging shock/turbulent boundary layer interaction flows. DLR Report IB 223-96 A 49.Google Scholar
Schultz, D. L. & Jones, T. V. 1973 Heat-transfer measurements in short-duration hypersonic facilities. AGARDograph 165.Google Scholar
Settles, G. S. & Dodson, L. J. 1994 Supersonic and hypersonic shock/boundary-layer interaction database. AIAA J. 32, 1377–1383.Google Scholar
Simeonides, G. & Haase, W. 1995 Experimental and computational investigations of hypersonic flow about compression ramps. J. Fluid Mech. 283, 17–42.Google Scholar
Smith, D. R. & Smits, A. J. 1994 The effects of streamline curvature and pressure gradient on the behaviour of turbulent boundary layers in supersonic flow. AIAA Paper 94-2227.Google Scholar
Smits, A. J. & Dussauge, J.-P. 1996 Turbulent Shear Layers in Supersonic Flow. AIP.Google Scholar
Stollery, J. L. S. & Coleman, G. T. 1975 A correlation between pressure and heat transfer distributions at supersonic and hypersonic speeds. Aeronaut. Q. 26, 304–311.Google Scholar
Wilcox, D. C. 1992 Dilatation–dissipation corrections for advanced turbulence models. AIAA J. 30, 2639–2646.Google Scholar