Hostname: page-component-76fb5796d-dfsvx Total loading time: 0 Render date: 2024-04-25T11:38:39.403Z Has data issue: false hasContentIssue false
  • English
  • Français

Corner effect and separation in transonic channel flows

Published online by Cambridge University Press:  31 May 2011

P. J. K. BRUCE ,
D. M. F. BURTON ,
N. A. TITCHENER  and
H. BABINSKY
P. J. K. BRUCE*
Affiliation:
Department of Engineering, University of Cambridge, Trumpington Street, Cambridge CB2 1PZ, UK
D. M. F. BURTON
Affiliation:
Department of Engineering, University of Cambridge, Trumpington Street, Cambridge CB2 1PZ, UK
N. A. TITCHENER
Affiliation:
Department of Engineering, University of Cambridge, Trumpington Street, Cambridge CB2 1PZ, UK
H. BABINSKY
Affiliation:
Department of Engineering, University of Cambridge, Trumpington Street, Cambridge CB2 1PZ, UK
*
†Present address: Department of Mechanical Engineering, Imperial College London. Email address for correspondence: p.bruce@imperial.ac.uk
Get access Rights & Permissions [Opens in a new window]

Abstract

An investigation into parameters affecting separation in normal shock wave/boundary layer interactions (SBLIs) has been conducted. It has been shown that the effective aspect ratio of an experimental facility (defined as δ*/tunnel width) is a critical factor in determining when shock-induced separation will occur. Experiments examining M∞ = 1.4 and 1.5 normal shock waves in a wind tunnel with a small rectangular cross-section have been performed and show that a link exists between the extent of shock-induced separation on the tunnel centre-line and the size of corner-flow separations. In tests where the corner-flows were modified ahead of the shock (through suction and vortex generators), the extent of separation around the tunnel centre-line was seen to vary significantly. These observations are attributed to the way corner flows modify the three-dimensional shock-structure and the impact this has on the magnitude of the adverse pressure gradient experienced by the tunnel wall boundary layers.

JFM classification

Boundary Layers: Boundary layer separation Aerodynamics: High-speed flow Compressible Flows: Shock waves
Type
Papers
Information
Journal of Fluid Mechanics , Volume 679 , 25 July 2011 , pp. 247 - 262
Copyright
Copyright © Cambridge University Press 2011

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.)

References

REFERENCES

Ackeret, J., Feldmann, F. & Rott, N. 1947 Investigations of compression shocks and boundary layers in gases moving at high speed. NACA Tech. Rep. TM1113.Google Scholar
Alber, I. E., Bacon, J. W., Masson, B. S. & Collins, D. J. 1973 An experimental investigation of turbulent transonic viscous-inviscid interactions. AIAA J. 11 (5), 620–627.CrossRefGoogle Scholar
Atkin, C. J. & Squire, L. C. 1992 A study of the interaction of a normal shock wave with a turbulent boundary layer at Mach numbers between 1.30 and 1.55. Eur. J. Mech. 11 (1), 93–118.Google Scholar
Burton, D. M. F., Babinsky, H. & Bruce, P. J. K. 2010 Experimental investigation into parameters governing corner interactions for transonic shock-wave/boundary-layer interactions. AIAA Paper 2010-0871.CrossRefGoogle Scholar
Chapman, D. R., Kuehn, D. M. & Larson, H. K. 1957 Investigation of separated flow in supersonic and subsonic streams with emphasis on the effects of transition. Technical note 3869. NACA, Washington.Google Scholar
Chriss, R. M., Hingst, W. R., Strazisar, A. J. & Keith, T. G. 1989 An LDA investigation of three-dimensional normal shock wave boundary-layer interaction. In Proc. Transonic Symposium: Theory, Application and Experiment, vol. 1, Part 2, pp. 741–764. NASA Langley Research Center.Google Scholar
Delery, J. 1985 Shock wave/turbulent boundary layer interaction and its control. Prog. Aerosp. Sci. 22 (4), 209–280.CrossRefGoogle Scholar
Doerffer, P., Hirsch, C., Dussauge, J.-P. & Babinsky, H. (Ed.) 2010 Unsteady Effects of Shock Wave induced Separation: 220 (Notes on Numerical Fluid Mechanics and Multidisciplinary Design), 1st edn. Springer.Google Scholar
Doerffer, P. & Szwaba, R. 2004 Shock wave boundary layer interaction control by streamwise vortices. In Proc. XXI ICTAM 15–21 August, Warsaw, Poland.Google Scholar
Dupont, P., Haddad, C., Ardissone, J.-P. & Debieve, J. F. 2005 Space and time organisation of a shock wave/turbulent boundary layer interaction. Aerosp. Sci. Technol. (9), 561–572.Google Scholar
Erdos, J. & Pallone, A. 1962 Shock-boundary layer interaction and flow separation. In Proc. Heat Transfer and Fluid Mechanics Institute, pp. 239–254.Google Scholar
Handa, T., Masuda, M. & Matsuo, K. 2005 Three-dimensional normal shock-wave/boundary-layer interaction in a rectangular duct. AIAA J. 43 (10), 2182–2187.Google Scholar
Inger, G. R. 1976 Analysis of transonic normal shock-boundary layer interaction and comparisons with experiments. Tech. Rep. Virginia Inst. and State Univ.CrossRefGoogle Scholar
Kooi, J. W. 1978 Influence of free-stream Mach Number on Transonic Shock-Wave Boundary-Layer Interaction. MP Tech. Rep. 78013 U. National Aerospace Laboratory NLR.Google Scholar
Nussdorfer, T. J. 1956 Some observations of shock-induced turbulent separation in supersonic diffusers. Tech. Rep.Google Scholar
Sajben, M., Morris, M. J., Bogar, T. J. & Kroutil, J. C. 1991 Confined normal-shock/turbulent-boundary-layer interaction followed by an adverse pressure gradient. AIAA J. 29 (12), 2115–2123.Google Scholar
Seddon, J. 1960 The flow produced by interaction of a turbulent boundary layer with a normal shock wave of strength sufficient to cause separation. Tech. Rep. 3502. Ministry of Technology ARC RM.Google Scholar
Titchener, N. & Babinsky, H. 2011 Micro-vortex generators applied to a flow-field containing a normal shock-wave and diffuser. AIAA J. 49 (5), 1046–1056.Google Scholar
Van Driest, E. R. 1951 Turbulent boundary layer in compressible fluids. J. Aeronaut. Sci. 18 (3), 1–20.Google Scholar
Weber, A., Schreiber, H.-A., Fuchs, R. & Steinert, W. 2002 3-D Transonic flow in a compressor cascade with shock-induced corner stall. J. Turbomach. 124, 358–366.Google Scholar
Zheltovodov, A., Dvorak, R. & Safarik, P. 1990 Shock wave/turbulent boundary layer interaction properties at transonic and supersonic speed conditions. Izvestiya SO AN SSSR 6, 31–42.Google Scholar