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Study of unsteady characteristics of flare-induced hypersonic shock-wave boundary-layer interaction flowfield with variation in γ

Published online by Cambridge University Press:  04 July 2016

S. B. Verma
S. B. Verma*
Affiliation:
DLR Lampoldshausen, Germany
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Abstract

Experimental work has been carried out to study the unsteady flow-field characteristics related to shock-wave/boundary-layer interaction. Tests were carried out on an axisymmetric configuration that has a semi-cone angle of 35° and a flare angle of 20°. Further influence of low γ gases (C02 and CF4) on the overall interaction process is also investigated. Both surface and off-surface analysis has been carried out. Off-surface study has been made with a laser schlieren system. The purpose of this study was to investigate the source of the unsteadiness related to such interactions. Two types of shock motions, namely, flapping and rippling could be identified for air, the relative importance of each of which is strongly dependent on the location within the interaction and on the type of test gas. Spectral analysis shows the large-scale motion of the separation bubble to be the main source of high amplitude fluctuations. However, the existence of separation bubble itself does not necessarily indicate the prevalence of unsteady flow conditions.

Type
Research Article
Information
The Aeronautical Journal , Volume 107 , Issue 1069 , March 2003 , pp. 149 - 158
Copyright
Copyright © Royal Aeronautical Society 2003 

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References

1. Kistler, A.L. Fluctuating wall pressure under a separated supersonic flow, J Acoustical Society of America, 1964, 36, (3), pp 543–550.Google Scholar
2. Muck, K., Andreopoulos, J. and Dussauge, J. Unsteady nature of shock-wave/turbulent boundary-layer interaction, AIAA Journal, 1988, 26, (2), pp. 179–187.Google Scholar
3. Bertin, J.J. Hypersonic aerothermodynamics, AIAA Education Series.Google Scholar
4. Charwat, A.F., Dewey, C.F., Roos, J.N. and Hitz, J.A. Investigation of separated flows, Part II; flow in cavity and heat t ransfer, J of Aeronautical Sciences, 1961, 28, (7), pp. 513–527.Google Scholar
5. Dolling, D.S. and Murphy, M.T. Unsteadiness of the separation shock wave structure in a supersonic compression ramp field, AIAA J, 1983, 21,(12), pp 1628–1634.Google Scholar
6. Horstman, C.C. and Owen, F.K. New diagnostic technique for the study of turbulent boundary layer separation, AIAA J, 1974, 12, (10), pp 1436–1438.Google Scholar
7. Maull, D.J. Hypersonic flow over axially symmetric spiked bodies, J Fluid Mechanics, 1960, 4, pp 584–592.Google Scholar
8. Verma, S.B. Detection of fluctuating density gradient flow field in shock wave boundary-layer interaction using laser Schlieren system, experiments in fluids, 2002, 32, (4), pp 527–531.Google Scholar
9. Verma, S.B. and Koppenwallner, G. Nature of shock-wave/boundary-layer interaction on a 12° ramp model. In: Wagner, S., Rist, U., Heinemann, H-J, Hilbig, R. (Eds), New results in numerical and experimental fluid mechanics III, Contributions to the 12th DGLR-Fach-Symposium der AG-STAB, University of Stuttgart, Germany, Springer-Verlag, pp 145–152, 2000.Google Scholar
10. Verma, S.B. and Koppenwallner, G. Unsteady separation in a flare induced hypersonic shock-wave boundary-layer interaction, J of Space craft and Rockets, 2002, 39, (3), pp. 467–470.Google Scholar
11. Funk, B.H. and Johnston, K.D. Laser Schlieren cross-beam measurements in a supersonic jet shear layer, AIAA J, 1970, 8, (11), pp 2074–2075.Google Scholar
12. Eigner, M. and Koppenwallner, G. Variable gamma testing, FESTIP Technology, HTG, 2000, Report 00 – 01.Google Scholar
13. Dolling, D.S. and Narlo, J.C. II Driving mechanism of unsteady separation shock motion in hypersonic interactive flow, AGARD-CP-428, Aerodynamics of Hypersonic Lifting Vehicles, 1987, April, pp 7 – 1 to 7–12.Google Scholar