Hostname: page-component-848d4c4894-nmvwc Total loading time: 0 Render date: 2024-07-05T10:40:04.590Z Has data issue: false hasContentIssue false
  • English
  • Français

Experiments on cruise propulsion with a hydrogen scramjet

Published online by Cambridge University Press:  04 July 2016

R. J. Stalker  and
A. Paull
R. J. Stalker
Affiliation:
Department of Mechanical Engineering , The University of Queensland , Queensland, Australia
A. Paull
Affiliation:
Department of Mechanical Engineering , The University of Queensland , Queensland, Australia
Get access Rights & Permissions [Opens in a new window]

Abstract

Measurements of drag have been made, in a shock tunnel, on a simple integrated vehicle-engine combination for hypersonic cruise with hydrogen scramjet propulsion. The test flow Mach number was 6·4, and the velocity was 2·45 kms-1. Zero drag, which is the necessary condition for cruise, was achieved as the equivalence ratio approached one. It was found that an analysis using established aerodynamic concepts was adequate for predicting drag in the case of no combustion. When combustion occurred results of direct connect experiments provided a qualitative guide to the measured levels of drag, and indicated that thrust nozzle combustion was taking place. An heuristic analysis is used to point to the important effect this may have on propulsive lift.

Type
Research Article
Information
The Aeronautical Journal , Volume 102 , Issue 1011 , January 1998 , pp. 37 - 44
Copyright
Copyright © Royal Aeronautical Society 1998 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1. Ferri, A. Review of problems in application of supersonic combustion, Aeronaut J, September 1964, 68, (645), pp 575–597.Google Scholar
2. Swithenbank, J. Hypersonic Air-Breathing Propulsion, Pergamon Press, Oxford, Progress in the Aerospace Sciences, Kuchemann, D. (Ed), 1967, 8, pp 229–294.Google Scholar
3. Billig, F.S. Research on supersonic combustion, J Prop and Power, 1993, 9,(4), pp 449–514.Google Scholar
4. Curran, E.T. and Heiser, W.H. Fluid phenomena inscramjet combustion systems. Annual reviews, Calif, Ann Rev Fluid Mech, 1996, 28, pp 323–360.Google Scholar
5. Guy, R.W. and Mackley, E.A. Initial windtunnel tests at Mach 4 and 7 of a hydrogen-burning, airframe-integrated scramjet. Presented at 4th Int Symp on Air Breathing Engines, Lake Beuna Vista, Florida, 1-6 April 1979.Google Scholar
6. Andrews, E.H. and Mackley, E.A. Nasa's hypersonic research engine project — a review, NASA TM 107759, October 1994.Google Scholar
7. Paull, A., Stalker, R.J. and Mee, D.J. Scramjet thrust measurement in a shock tunnel, Aeronaut J, April 1995, 99, (984), pp 161–163.Google Scholar
8. Paull, A., Stalker, R.J. and Mee, D.J. Experiments on supersonic combustion ramjet propulsion in a shock tunnel, J Fluid Mech, 1995, 296, pp 159–183.Google Scholar
9. Küchemann, D. and Weber, J. An Analysis of Some Performance Aspects of Various Types of Aircraft Designed to Fly Over Different Ranges at Different Speeds, Pergamon Press, Oxford, Progress in Aeronautical Sciences, 1968, 9, pp 329–456.Google Scholar
10. Anderson, D.A. and Nangia, R.K. Comparison of numerical and experimental “conical” flowrields in supersonic corners with compression and/or expansion, Aeronaut Q, 1977, 28, (4), pp 293–306.Google Scholar
11. Hayes, W.D. and Probstein, R. Hypersonic Flow Theory, Academic Press, New York, 1959, p 296.Google Scholar
12. He, Y. and Morgan, R.G. Transition of compressible high enthalpy boundary layer flow over a flat plate, Aeronaut J, February 1994, 98, (972), pp 25–34.Google Scholar
13. Stalker, R.J., Morgan, R.G. and Paull, A. A shock tunnel investiga tion of scramjet performance with partially premixed combustion. AIAA paper no 96-4534. Presented at AIAA 7th Int Space Planes & Hypersonic Sys & Tech Conf 18-22 November, Norfolk, VA, 1996.Google Scholar
14. Wendt, M.N. and Stalker, R.J. Transverse and parallel injection of hydrogen with supersonic combustion in a shock tunnel, Shock Waves J, 1996, 6, pp 53–59.Google Scholar
15. Mee, J., Daniel, W.J.T. and Simmons, J.M. Three-component force balance for flows of millsecond duration. AIAA J, 1996, 34, (3), pp 590–595.Google Scholar
16. Pulsonetti, M.V. and Stalker, R.J. A study of scramjet scaling. AIAA Paper No 96-4533. Presented at AIAA 7th Int Space Planes and Hypersonic Sys & Tech Conf, 18-22 November, Norfolk, VA, 1996.Google Scholar