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Mach 4 and Mach 8 axisymmetric nozzles for a high-enthalpy shock tunnel

Published online by Cambridge University Press:  04 July 2016

P. A. Jacobs  and
R. J. Stalker
P. A. Jacobs
Affiliation:
Institute for Computer Applications in Science and Engineering, NASA Langley Research Center, USA
R. J. Stalker
Affiliation:
Department of Mechanical Engineering, University of Queensland, Australia
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Abstract

This study examines the performance of two axisymmetric nozzles which were designed to produce uniform, parallel flow with nominal Mach numbers of 4 and 8. A free-piston-driven shock tube was used to supply the nozzle with high-temperature, high-pressure test gas. The inviscid design procedure treated the nozzle expansion in two stages. Close to the nozzle throat, the nozzle wall was specified as conical and the gas flow was treated as a quasi-one-dimensional chemically-reacting flow. At the end of the conical expansion, the gas was assumed to be calorically perfect and a contoured wall was designed (using Method-of-Characteristics) to convert the source flow into a uniform and parallel flow at the end of the nozzle. Performance was assessed by measuring Pitot pressures across the exit plane of the nozzles and, over the range of operating conditions examined, the nozzles produced satisfactory test flows. However, there were flow disturbances in the Mach 8 nozzle flow that persisted for significant times after flow initiation.

Type
Research Article
Information
The Aeronautical Journal , Volume 95 , Issue 949 , November 1991 , pp. 324 - 334
Copyright
Copyright © Royal Aeronautical Society 1991 

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Footnotes

*

Current address: Department of Mechanical Engineering, University of Queensland.

References

1. Stalker, R. J. Hypervelocity aerodynamics with chemical nonequilibrium. Annual Review of Fluid Mechanics, 1989, 21, pp 37–60.Google Scholar
2. Hornung, H. G. 28th Lanchester Memorial Lecture — Experimental real-gas hypersonics. Aeronaut J, 1988, 92, pp 379–389, December.Google Scholar
3. Jacobs, P. A., Rogers, R. C, Weidner, E. H., and Bittner, R. D. Flow establishment in a generic scramjet combustor. AIAA Paper 90-2096, 1990.Google Scholar
4. Davies, W. R. and Bernstein, L. Heat transfer and transition to turbulence in the shock-induced boundary layer on a semi-infinite flat plate, J Fluid Mech, 1969, 36, pp 87–112.Google Scholar
5. Morgan, R. G., Paull, A., Stalker, R. J., Jacobs, P. A., Morris, N., Stringer, I., and Brescianini, C. Shock Tunnel Studies of Scramjet Phenomena. NASA CR 181721, 1988.Google Scholar
6. Jacobs, P. A. A Mach 4 Nozzle for Hypervelocity Flow, Department of Mechanical Engineering Report 9/89, University of Queensland, 1989.Google Scholar
7. Jacobs, P. A. A Mach 8 Nozzle for The T4 Shock Tunnel. Department of Mechanical Engineering Report 12/89, University of Queensland, 1989.Google Scholar
8. Jacobs, P. A., and Stalker, R. J. Design of Axisymmetric Nozzles for Reflected Shock Tunnels. Department of Engineering Report 1/89, University of Queensland, 1989.Google Scholar
9. Liepmann, H. W. and Roshko, A. Elements of Gasdynamics, John Wiley and Sons, New York, 1957.Google Scholar
10. Anderson, J. D. Modern Compressible Flow: with Historical Perspective, McGraw-Hill, New York, 1982.Google Scholar
11. Jacobs, P. A. Transient, hypervelocity flow in an axisymmetric nozzle. AIAA Paper 91-0295, 1991.Google Scholar
12. Amann, H. O. Experimental study of the starting process in a reflection nozzle. The Physics of Fluids Supplement I, pp I–150-I-153, 1969.Google Scholar
13. Smith, C. E. The starting process in a hypersonic nozzle, J Fluid Mech, 1966, 24, pp 625–640.Google Scholar
14. Gregorenko, V. L., Naumov, A. M., and Hvostor, N. I. Influence of non-stationary flow effects on test time of a hypersonic shock tunnel, Scientific Notes of the Central Hydro-dynamic Institute, 1984, 15, (5).Google Scholar
15. Britain, A. B. and Vasil'ev, E. I. Peculiarities of the formation of the flow in a shaped shock-tube nozzle, Soviet Physics Doklady, 1985, 30, (3), pp 199–201.Google Scholar
16. Hannemann, K. Design of an Axisymmetric, Contoured Nozzle for the HEG. Technical Report, DLR-FB90-04, DLR, 1990.Google Scholar
17. Mudford, N. R., Stalker, R. J., and Shields, I. Hypersonic nozzles for high enthalpy nonequilibrium flow. Aeronaut Q, 1980, 31, (2), pp 113–131.Google Scholar
18. Zonars, D. Nonequilibrium regime of airflows in contoured nozzles; theory and experiment. AIAA J, 1967, 4, (1), pp 57–63.Google Scholar
19. Lordi, J. A., Mates, R. E., and Mosselle, J. R. Computer program for the numerical solution of nonequilibrium expansions of reacting gas mixtures. NASA CR 472, 1966.Google Scholar
20. Harris, C. J. Comment on “Nonequilibrium effects on high-enthalpy expansion of air”. AIAA J, 1966, 4, (6), pp 1148.Google Scholar
21. Jacobs, P. A. and Gourlay, C. M. An interactive method-of-characteristics program for gas-dynamic calculations, Int J Appl Eng Educ, 1991, 7, (3).Google Scholar
22. Forsythe, G. E., Malcolm, M. A., and Moler, C. B. Computer methods for Mathematical Computations, Prentice-Hall, Engle-wood Cliffs, N. J., 1977.Google Scholar
23. Lukasiewicz, J. Experimental Methods of Hypersonics, Marcel Dekker, New York, 1973.Google Scholar
24. Korte, J. J. and McRae, D. S. Explicit upwind algorithm for the parabolised Navier-Stokes equations. AIAA Paper 88-0716, 1988.Google Scholar
25. Korte, J. J. An explicit, upwind algorithm for solving the parabolised Navier-Stokes equations. Ph. D. Dissertation, North Carolina State University, 1989.Google Scholar