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A gun tunnel investigation of hypersonic free shear layers in a planar duct

Published online by Cambridge University Press:  26 April 2006

D. R. Buttsworth ,
R. G. Morgan  and
T. V. Jones
D. R. Buttsworth
Affiliation:
Department of Mechanical Engineering, University of Queensland, Queensland 4072, Australia Department of Engineering Science, University of Oxford, Parks Road, Oxford OX1 3PJ, UK
Address for correspondence
R. G. Morgan
Affiliation:
Department of Mechanical Engineering, University of Queensland, Queensland 4072, Australia
T. V. Jones
Affiliation:
Department of Engineering Science, University of Oxford, Parks Road, Oxford OX1 3PJ, UK
Address for correspondence
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Abstract

An experimental investigation of high Mach number free shear layers has been undertaken. The experiments were performed using a Mach 7 gun tunnel facility and a planar duct with injection from the base of a central strut producing a Mach 3 flow parallel to the gun tunnel stream. This configuration is relevant to the development of efficient scramjet propulsion, and the gun tunnel Mach number is significantly higher than the majority of previous supersonic turbulent mixing layer investigations reported in the open literature. Schlieren images and Pitot pressure measurements were obtained at four different convective Mach numbers ranging from 0 to 1.8. Only small differences between the four cases were detected, and the relatively large high-speed boundary layers at the trailing edge of the struct injector appear to strongly influence the shear layer development in each case. The Pitot pressure measurements indicated that, on average, the free shear layers all spread into the Mach 3 stream at an angle of approximately 1.4°, while virtually no spreading into the Mach 7 stream was detected until all of the low-speed stream was entrained. The free shear layers were simulated using a PNS code; however, the experimentally observed degree of spreading rate asymmetry could not be fully predicted with the k−ε turbulence model, even when a recently proposed compressibility correction was applied.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 299 , 25 September 1995 , pp. 133 - 152
Copyright
© 1995 Cambridge University Press

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References

Anderson, G., Kumar, A. & Erdos, J. 1990 Progress in hypersonic combustion technology with computation and experiment. AIAA Paper 90-5254.
Bakos, R. J. & Morgan, R. G. 1992 Axisymmetric scramjet thrust production. 11th Australasian Fluid Mechanics Conference, pp. 295–298.
Birch, S. F. & Eggers, J. E. 1973 A critical review of the experimental data for developed free turbulent shear layers. In Free Turbulent Shear Flows, vol. 1, NASA SP-321, pp. 11–40.
Blumen, W., Drazin, D. G. & Billings, D. F. 1975 Shear layer instability of an inviscid compressible fluid. Part 2. J. Fluid Mech. 71, 305–316.Google Scholar
Bogdanoff, D. 1983 Compressibility effects in turbulent shear layers. AIAA J. 21, 926–927.Google Scholar
Brescianini, C. P. 1992a An investigation of the wall-injected scramjet. PhD Thesis, Department of Mechanical Engineering, University of Queensland.
Brescianini, C. P. 1992b Modified. K-é model for compressible free shear flows AIAA J. 30, 2161–2163.Google Scholar
Brescianini, C. P. & Morgan, R. G. 1992 An investigation of a wall-injected scramjet using a shock tunnel. AIAA Paper 92-3965.
Brescianini, C. P. & Morgan, R. G. 1993 Numerical modeling of wall-injected scramjet experiments. J. Propulsion Power 9, 169–175.Google Scholar
Brown, G. L. & Roshko, A. 1974 The density effects and large structure in turbulent mixing layers. J. Fluid Mech. 64, 775–816.Google Scholar
Buttsworth, D. R. 1994 Shock induced mixing and combustion in scramjets. PhD Thesis, Department of Mechanical Engineering, The University of Queensland.
Cain, T. M. 1991 An experimental study of underexpanded jets. D.Phil. thesis, Department of Engineering Science, University of Oxford.
Chinzei, N., Masuya, G., Komuro, T., Murakami, A. & Kudou, K. 1986 Spreading of two-stream supersonic turbulent mixing layers. Phys. Fluids 29, 1345–1347.Google Scholar
Clemens, N. T. & Mungal, M. G. 1992 Two- and three-dimensional effects in the supersonic mixing layer. AIAA J. 30, 973–981.Google Scholar
Clemens, N. T. & Mungal, M. G. 1995 Large-scale structure and entertainment in the supersonic mixing layer. J. Fluid Mech. 284, 171–216.Google Scholar
Dimotakis, P. E. 1991 Turbulent free shear layer mixing and combustion. In Progress in Astronautics and Aeronautics, Vol. 137: High-Speed Flight Propulsion Systems (ed. S. N. B. Murthy & E. T. Curran) pp. 265–340. AIAA.
Drummond, J. P., Carpenter, M. H. & Riggins, D. W. 1991 Mixing and mixing enhancement in supersonic reacting flowfields. In Progress in Astronautics and Aeronautics, Vol. 137: High-Speed Flight Propulsion Systems (ed. S. N. B. Murthy & E. T. Curran) pp. 383–455. AIAA.
Elliott, G. S. & Samimy, M. 1990 Compressibility effects in free shear layers. Phys. Fluids A 2, 1231–1240.Google Scholar
Elliott, G. S., Samimy, M. & Arnette, S. A. 1992 Study of compressible mixing layers using filtered Rayleigh scattering based visualizations. AIAA J. 30, 2567–2569.Google Scholar
Erdos J., Tamango, J., Bakos, R. & Trucco, R. 1992 Experiments on shear layer mixing at hypervelocity conditions. AIAA Paper 92-0628.
Goebel, S. G. & Dutton, J. C. 1991 Experimental study of compressible turbulent mixing layers. AIAA J. 29, 538–546.Google Scholar
Gropengiesser, H. 1970 Study of the stability of boundary layers in compressible fluids. NASA TT-F-12.
Hall, J. L., Dimotakis, P. E. & Roseman, H. 1993 Experiments in nonreacting compressible shear layers, AIAA J. 31, 2247–2254.Google Scholar
Kwok, K. T., Andrew, P. L., Ng, W. F. & Schetz, J. A. 1991 Experimental investigation of a supersonic shear layer with slot injection of helium, AIAA J. 29, 1426–1435.Google Scholar
Morris, N. A., Buttsworth, D. R., Brescianini, C. P. & Jones, T. V. 1995 An experimental and computational study of moderately underexpanded rocket exhaust plumes in a co-flowing hypersonic free stream. AIAA Paper 95-6127.
Papamoschou, D. 1991 Structure of the compressible turbulent shear layer. AIAA J. 29, 680–681.Google Scholar
Papamoschou, D. & Roshko, A. 1988 The compressible turbulent shear layer: an experimental study. J. Fluid Mech. 197, 453–477.Google Scholar
Ragab, S. A. & Wu, J. L. 1989 Linear instabilities in two-dimensional compressible mixing layers. Phys. Fluids A 1, 957–966.Google Scholar
Samimy, M. & Elliott, G. S. 1990 Effects of compressibility on the characteristics of free shear layers. AIAA J. 28, 439–445.Google Scholar
Samimy, M., Reeder, M. F. & Elliott, G. S. 1990 Compressibility effects on large structures in free shear flows. Phys. Fluids A 4, 1251–1258.Google Scholar
Sandham, N. D. & Reynolds, W. C. 1990 Compressible mixing layer: linear theory and direct simulation. AIAA J. 28, 618–624.Google Scholar
Shau, Y. R. & Dolling, D. S. 1992 Exploratory study of turbulent structure of a compressible shear layer using fluctuating Pilot pressure measurements.. Exp. Fluids 12, 293–306.Google Scholar
Stollery, J. L. 1967 Heat transfer at hypersonic speeds — a survey of recent and current experiments in the imperial college hypersonic gun tunnel. Aeronautical Research Council, ARC 29 611, HMT 166.
Tang, W., Komerath, N. M. & Sankar, L. N. 1990 Numerical simulation of the growth of instabilities in supersonic free shear layers. J. Propulsion Power 6, 455–460.Google Scholar
White, F. M. 1991 Viscous Fluid Flow, 2nd edn., p. 514. McGraw-Hill.
Zhuang, M., Kubota, T. & Dimotakas, P. E. 1988 On the instability of inviscid, ćompressible free shear layers. AIAA Paper 88-3538.