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An experimental study of the interaction of an unsteady shock with a turbulent boundary layer at Mach numbers of 1.3 and 1.5

Published online by Cambridge University Press:  04 July 2016

J. A. Edwards  and
L. C. Squire
J. A. Edwards
Affiliation:
Rolls-Royce Research Fellow, Wolfson College, Cambridge University
L. C. Squire
Affiliation:
Reader in Engineering, Cambridge University Engineering Department
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Abstract

In this paper the results are given of an experimental investigation into the flow development and the surface pressures in an unsteady shock boundary layer interaction at Mach numbers of 1.3 and 1.5. The experiment is one in which a naturally grown turbulent boundary layer on the tunnel walls is disturbed by a normal shock wave spanning the test section of the tunnel. The shock wave is oscillated by a periodic pressure disturbance in the tunnel diffuser far downstream of the interaction. Both instantaneous (spatially averaged) and time averaged results for the surface pressures are presented. These results are used to study the flow development and phase changes through the interaction over a frequency range from 34 to 167 Hz. This frequency range was chosen to cover the range of parameters likely to occur in conditions corresponding to stall flutter in the compressor fans of large bypass engines.

Type
Research Article
Information
The Aeronautical Journal , Volume 97 , Issue 970 , December 1993 , pp. 337 - 348
Copyright
Copyright © Royal Aeronautical Society 1993 

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Footnotes

†

Currently DRA W7 Division, Fort Halstead and visiting fellow, College of Aeronautics, Cranfield.

References

1. Tijdeman, H. Investigations of the Transonic Flow Around Oscillating Aerofoils, Nationaal Lucht-en Ruimtevaartlaboratorium, Amsterdam, The Netherlands, NLR TR 77090, December 1977.Google Scholar
2. Sabjen, M., Kroutil, J.C. and Chen, C.P. A high-speed schieren investigation of diffuser flows with dynamic distortion, AIAA Paper 77-875, 1977.Google Scholar
3. Chen, C.P., Sabjen, M. and Kroutil, J.C. Shock-wave oscillations in a transonic diffuser flow, AIAA J, 1979, 17, pp 1076–1083.Google Scholar
4. Sabjen, M. and Kroutil, J.C. Effects of initial boundary-layer thickness on transonic diffuser flows, AIAA J, November 1981, 19, pp 1386–1393.Google Scholar
5. Sabjen, M., Bogar, T.J. and Kroutil, J.C. Forced oscillation experiments in supercritical diffuser flows with applications to ramjet instabilities, AIAA Paper 811487, 1981.Google Scholar
6. Bogar, T.J., Sabjen, M. and Kroutil, J.C. Characteristic frequencies of transonic diffuser flow oscillations, AIAA J, 1983, 21, pp 1231–1240.Google Scholar
7. Richey, G.K. and Adamson, T.C. Analysis of unsteady transonic channel flow with shock waves, AIAA J, August 1976, 14, pp 1054–1061.Google Scholar
8. Messiter, A.F. and Adamson, T.C. Asymptotic solutions for nonsteady transonic channel flows, Symposium Transsonicum II, Oswatisch, K. and Rues, D. (eds) Springer-Verlag, 1976, pp 41–48.Google Scholar
9. Chan, J.S.-K. and Adamson, T.C. Unsteady transonic flows with shock waves in an asymmetric channel, AIAA J, April 1978, 16, pp 377–384.Google Scholar
10. Adamson, T.C., Messiter, A.F. and Liou, M.S. Large amplitude shock-wave motion in two-dimensional transonic channel flow, AIAA J, December 1978, 16, pp 1240–1247.Google Scholar
11. Messiter, A.F. and Adamson, T.C. Forced oscillations of transonic channel and inlet flows with shock waves, AIAA J, November 1984, 22, pp 1590–1599.Google Scholar
12. Whitehead, D.S. The Calculation of Steady and Unsteady Transonic Flows in Cascades, Cambridge University Engineering Department Report CUED/A-Turbo/TR 118,1982.Google Scholar
13. Barton, H.A. Naqvi, M.M. and Newton, S.G. An evaluation of a finite element calculation method for unsteady transonic flows against cascade test data, IUTAM Symposium Unsteady Aerodynamics of Turbomachines and Propellers, Cambridge, September 1984.Google Scholar
14. Liou, M-S. and Coakley, T.J. Numerical simulations of unsteady transonic flow in diffusers, AIAA J, August 1984, 22, pp 1139–1145.Google Scholar
15. Edwards, J.A. and Squire, L.C. Experimental observations on an unsteady, normal shock/boundary layer interaction, AGARD CP 401, Transonic and Supersonic Phenomena in Turbomachines, September 1986.Google Scholar
15. Bryanston-Cross, P.J., Edwards, J.A. and Squire, L.C. Measurements in an unsteady two-dimensional shock/boundary-layer interaction. IUTAM Symposium, Unsteady Aerodynamics of Turbomachines and Propellers, Cambridge, September 1984.Google Scholar
17. Atkin, C.J. and Squire, L.C. A study of a normal shock wave with a turbulent boundary layer at mach numbers between 1.30 and 1.55, Eur J Mech,B/Fluids, 1992, 11, pp 93–118.Google Scholar
18. Atkin, C.J. Numerical simulation of unsteady shock/boundary-layer interactions, submitted to AIAA J for publication.Google Scholar
19. Sabjen, M. and Crites, R.C. Real time optical measurement of time dependent shock position, AIAA J, 1979, 17, pp 910–912.Google Scholar
20. Sawyer, W.G. and Long, C.J. A Study of Normal Shock-Wave Turbulent Boundary-Layer Interaction at Mach numbers of 1.3, 1.4 and 1.5, RAE TR 82099, 1 982.Google Scholar
21. Dolling, D.S. and Narlo II, J.C. Driving mechanism of unsteady shock motion in hypersonic interactive flow, AGARD Conference on Aerodynamics of Hypersonic Lifting Vehicles, Bristol, April 1987.Google Scholar
22. Hurrell, H.G., Analysis of shock motion in ducts during disturbances in downstream pressure, NACA TN 4090, 1957.Google Scholar