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High enthalpy, hypervelocity flows of air and argon in an expansion tube

Published online by Cambridge University Press:  04 July 2016

A. J. Neely ,
R. J. Stalker  and
A. Paull
A. J. Neely
Affiliation:
Department of Mechanical Engineering, The University of Queensland, Australia
R. J. Stalker
Affiliation:
Department of Mechanical Engineering, The University of Queensland, Australia
A. Paull
Affiliation:
Department of Mechanical Engineering, The University of Queensland, Australia
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Abstract

An expansion tube with a free piston driver has been used to generate quasi-steady hypersonic flows in argon and air at flow velocities in excess of 9 km/s. Irregular test flow unsteadiness has limited the performance of previous expansion tubes, and it has been found that this can be avoided by attention to the interaction between the test gas accelerating expansion and the contact surface in the primary shock tube. Test section measurements of pitot pressure, static pressure and flat plate heat transfer are reported. An approximate analytical theory has been developed for predicting the velocities achieved in the unsteady expansion of the ionising or dissociating test gas.

Type
Research Article
Information
The Aeronautical Journal , Volume 95 , Issue 946 , July 1991 , pp. 175 - 186
Copyright
Copyright © Royal Aeronautical Society 1991 

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References

1. Stalker, R. J. Hypervelocity aerodynamics with chemical nonequilibrium, Ann Rev Fluid Mech, 1989, 21, pp 37–60.Google Scholar
2. Resler, E. L. and Bloxsom, D. E. Very High Mach Number Flows By Unsteady Flow Principles, Cornell University Graduate School of Aeronautical Engineering, limited circulation monograph, January 1952.Google Scholar
3. Trimpi, R. L. A Preliminary Theoretical Study of the Expansion Tube, A New Device For Producing High-Enthalpy Short- Duration Hypersonic Gas Flows, NASA Technical Report R-133, 1962.Google Scholar
4. Jones, J. J. Some performance characteristics of the LRC 3¾ inch pilot tube using an unheated hydrogen driver, Fourth Hypervelocity Techniques Symposium, Tullahoma, Tennessee, 1965, pp 7–26.Google Scholar
5. Spurk, J. H. Design, operation, and preliminary results of the BRL expansion tube, Fourth Hypervelocity Techniques Symposium, Tullahoma, Tennessee, 1965, pp 112–114.Google Scholar
6. Norfleet, G. D., Lacey, J. J. and Whitfield, J. D. Results of an experimental investigation of the performance of an expansion tube, Fourth Hypervelocity Techniques Symposium, Tullahoma, Tennessee, 1965, pp 49–110.Google Scholar
7. Miller, C. G. Operational Experience in the Langley Expansion Tube with Various Test Gases, NASA TM 78637, 1977.Google Scholar
8. Stalker, R. J., Paull, A. and Stringer, I. Experiments on an Expansion Tube with a Free Piston Driver—Phase 1, Department of Mechanical Engineering Report, The University of Queensland, 1987.Google Scholar
9. Paull, A., Stalker, R. J. Experiments on an Expansion Tube with a Free Piston Driver—Phase 2, Department of Mechanical Engineering report, The University of Queensland, 1989.Google Scholar
10. Paull, A. Theoretical Analysis of Test Conditions in an Expansion Tube, Department of Mechanical Engineering report, The University of Queensland, 1989.Google Scholar
11. Paull, A. and Stalker, R. J. The effect on an acoustic wave as it traverses an unsteady expansion, Phys Fluids A (accepted for publication).Google Scholar
12. Moore, J. A. Description and Initial Operating Performance of the Langley 6-inch Expansion Tube Using Heated Helium Driver Gas, NASA TM X-3240, 1975.Google Scholar
13. Lighthill, M. J. Dynamics of a dissociating gas. Part I Equilibrium flow, J Fluid Mech, January 1957, 2, (1), pp 1–32.Google Scholar
14. Stalker, R. J. An Approximate Theory of Equilibrium One- Dimensional Steady And Unsteady Expanding Flows of an Ideal Dissociating Gas, N.R.C. MT-45, National Research Council of Canada, Ottawa, June 1961.Google Scholar
15. Logan, P. F., Stalker, R. J. and McIntosh, M. K. A shock tube study of radiative energy loss from an argon plasma, J Phys D: Appl Phys, 1977, 10, pp 323–337.Google Scholar
16. Schultz, D. L. and Jones, T. V. Heat Transfer Measurements In Short Duration Hypersonic Facilities, AGARDograph No. 165, February 1973.Google Scholar
17. Morgan, R. G. and Stalker, R. J. Shock tunnel measurements of heat transfer in a model scramjet, J Spacecraft Rockets, Sept- Oct 1986, 23, (5), pp 470–475.Google Scholar
18. Eckert, E. R. G. Engineering relations for friction and heat transfer to surfaces in high velocity flow, August 1955, J Aeronaut Sci, pp 585–587.Google Scholar
19. Cox, R. N. and Crabtree, L. F. Elements of Hypersonic Aerodynamics, English Universities Press, London, 1965.Google Scholar
20. White, F. M. Viscous Fluid Flow, McGraw-Hill, New York, 1974.Google Scholar
21. 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