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Transition of compressible high enthalpy boundary layer flow over a flat plate

Published online by Cambridge University Press:  04 July 2016

Y. He  and
R. G. Morgan
Y. He
Affiliation:
Department of Mechanical Engineering, University of Queensland, Australia
R. G. Morgan
Affiliation:
Department of Mechanical Engineering, University of Queensland, Australia
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Abstract

This paper presents the results of an experimental investigation into the characteristics of boundary layer transition to turbulence in hypervelocity air flows. A series of experiments was conducted using a flat plate model, equipped with static pressure and thin film heat transfer transducers, in a free piston shock tunnel. Transition was observed in the stagnation enthalpy range of 2·35 to 19·2 MJ/kg. The transition Reynolds number correlates well with the unit Reynolds number through a simple empirical relation. The influences of Mach number, pressure and wall cooling are examined. The measured heat transfer rates in laminar and turbulent regions are compared with empirical predictions. Freestream disturbances of the test flow were also measured and analysed.

Type
Research Article
Information
The Aeronautical Journal , Volume 98 , Issue 972 , February 1994 , pp. 25 - 34
Copyright
Copyright © Royal Aeronautical Society 1994 

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Footnotes

*

Currently at Department of Aerospace and Mechanical Engineering, University College, University of New South Wales, Australia.

References

1. Kendall, J.M. Wind tunnel experiments relating to supersonic and hypersonic boundary-layer transition, AIAA J, 1975, 13, (3), pp 290–299.Google Scholar
2. Reshotko, E. Boundary-layer stability and transition, Ann Rev Fluid Mech, 1976, 8, pp 311–349.Google Scholar
3. Van driest, E.R. Calculations of the stability of the laminar boundary layer in a compressible fluid on a flat plate with heat transfer, J Aero Sci, 1952, 19, (13), pp 801–812.Google Scholar
4. Mack, L.M. Boundary Layer Stability Theory, AGARD, Rep no. 1709, 1984.Google Scholar
5. Stetson, K.F. and Kimmel, R.L. On hypersonic boundary layer stability AIAA-92-0737, 30th Aerospace Sciences Meeting and Exhibit, 6-9 January 1992, Reno, NV.Google Scholar
6. Seddougui, S.O., Bowles, R.I. and Smith, F.T. Surface Cooling Effects on Compressible Boundary Layer Instability, NASA Contractor Report 182003, ICASE Report No. 9019, 1990.Google Scholar
7. Deem, R.E. and Murphy, J.S. Flat plate boundary layer transition at hypersonic speeds, AIAA Paper 65128, 1965.Google Scholar
8. Ross, R. Influence of total temperature on transition in supersonic flow, AIAA J, 1973, 11, (4), pp 563–565.Google Scholar
9. Demetriades, A. New experiments on hypersonic boundary layer stability including wall temperature effects, In: Proceedings of the 1978 Heat Transfer and Fluid Mechanics Institute, Washington, Emery, A.F. and Depew, C.A. (eds), Stanford University Press, 26-28 June 1968, pp 39–55.Google Scholar
10. Stetson, K.F. and Rushton, G.H. Shock tunnel investigation of boundary-layer transition at M = 5·5, AIAA J, 1967, 451, (5), pp 899–906.Google Scholar
11. Richards, B.E. and Stollery, J.L. Further experiment on transition reversal at hypersonic speeds, AIAA J, 1966, 4, (12), pp 2224–2226.Google Scholar
12. Cary, A.M. Jr Turbulent boundary layer heat transfer and transition measurements for cold wall conditions at Mach 6, AIAA J, 1968, 6, (5), pp 958–959.Google Scholar
13. Stalker, R.J. and Morgan, R.G. The University of Queensland free piston shock tunnel T4, initial operation and preliminary calibration, In: Proceedings of 43rd Australian National Space Engineering Symposium, Adelaide, 1988.Google Scholar
14. Stalker, R.J. and Crane, K.C.A. Driver gas contamination in a high-enthalpy reflected shock tunnel, AIAA J, 1978, 16, (3), pp 277–279.Google Scholar
15. McIntosh, M.K. Computer program for the numerical calculation of frozen and equilibrium conditions in shock tunnels, Department of Physics, Australian National University, Canberra, Australia, September 1968.Google Scholar
16. Lordi, J.A., Mates, R.E. and Moselle, J.R. Computer program for the numerical solution of nonequilibrium expansions of reacting gas mixtures, NASA CR 472, 1966.Google Scholar
17. Chen, F.J., Malik, M.R. and Beckwith, I.E. Boundary layer transition on a cone and flat plate at Mach 3·5, AIAA J, 1989, 27, (6), pp 687–693.Google Scholar
18. Pate, S.R. Effects of wind tunnel disturbances on boundary layer transition with emphasis on radiated noise: a review, 1lth Aerodynamic Testing Conference, Colorado Springs, Colorado, 18-20 March 1980.Google Scholar
19. Wells, C.S. Jr Effects of freestream turbulence on boundary layer transition, AIAA J, 1967, 5,(1), pp 172–174.Google Scholar
20. Schubauer, G.B. and Skramstad, H.K. Laminar boundary layer oscillations and transition on a flat plate, J Aero Sci, 1947, 14, pp 69–76.Google Scholar
21. Boltz, F.W., Kenyon, G.C. and Allen, C.Q. The boundary layer transition characteristics of two bodies of revolution, a flat plate and an unswept wing in a low turbulence wind tunnel, NASA D309, 1960.Google Scholar
22. Owen, F.K. and Horstman, C.C. Comparison of wind tunnel transition and free stream disturbance measurements, AIAA J, 1975, 13, (3), pp 266–269.Google Scholar
23. Pilipenko, A.A. and Shapovalov, G.K. Effect of model vibration on transition from laminar to turbulent boundary layer flow, Fluid Mechanics-Soviet Research, 1988, 17, (4), pp 68–76.Google Scholar
24. Eckert, E.R.G. Engineering relations for skin frictions and heat transfer to surface in high velocity flow, J Aero Sci, 1955, 22, pp 585–587.Google Scholar
25. Stollery, J.L. and Coleman, G.T. A correlation between pressure and heat transfer at supersonic and hypersonic speeds, Aeronaut Q, 1975, 26, pp 304–315.Google Scholar
26. Dhawan, S. and Narasimha, R. Some properties of boundary layer flow during the transition from laminar to turbulent motion, J Fluid Mech, 1958, 3, pp 428–436.Google Scholar
27. Narasimha, R. The laminar-turbulent transition zone in the boundary layer, Prog Aero Sci 22, 1985, pp 29–80.Google Scholar
28. Abu-Ghannam, B.J. and Shaw, R. Natural transition of boundary layers, the effects of turbulence, pressure gradient, and flow history, J Mech Eng Sci, 1980, 22, (5), pp 213–228.Google Scholar
29. Germain, P., Cummings, E., and Hornung, H., Transition on a sharpcone at high enthalpy; new measurements in the shock tunnel T5 at Galcit, 31st Aerospace Sciences Meeting and Exhibit, 11-14 January 1993, Reno, NV.Google Scholar
30. Nagel, A.L. Analysis of the unit reynolds number effect in hypersonic flat plate boundary layer transition, In: Proceedings of the 1968 Heat Transfer and Fluid Mechanics Institute, Amery, A.F. and De-pew, C.A. (eds). Stanford University Press, 1968, pp 51–64.Google Scholar
31. Stollery, J.L. Heat transfer at hypersonic speeds — a survey of recent and current experiments in the Imperial College hypersonic guntunnel, ARC. 29611, December 1967.Google Scholar
32. Pate, S.R. and Schueler, C.J. Radiated aerodynamic noise effects on boundary layer transition, AIAA J, 1969, 7, (3), pp 450–457.Google Scholar
33. Owen, F.K. Transition experiments on a flat plate at subsonic and supersonic speeds, AIAA J, 1970, 8, (3), pp 518–523.Google Scholar
34. Bowcutt, K.G., Anderson, J.D. and Capriotti, D. Viscous optimized hypersonic waveriders, Paper 87-0272, 1987.Google Scholar