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Scramjet thrust measurement in a shocktunnel

Published online by Cambridge University Press:  04 July 2016

A. Paull,
R. J. Stalker and
D. J. Mee
A. Paull
Affiliation:
Department of Mechanical Engineering, The University of Queensland, Brisbane, Australia
R. J. Stalker
Affiliation:
Department of Mechanical Engineering, The University of Queensland, Brisbane, Australia
D. J. Mee
Affiliation:
Department of Mechanical Engineering, The University of Queensland, Brisbane, Australia
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Extract

This note reports tests in a shock tunnel in which afully integrated scramjet configuration produced netthrust. The experiments not only showed that impulsefacilities can be used for assessing thrustperformance, but also were a demonstration of theapplication of a new technique(1) to themeasurement of thrust on scramjet configurations inshock tunnels. These two developments are ofsignificance because scramjets are expected tooperate at speeds well in excess of 2 km/s, andshock tunnels offer a means of generating high Machnumber flows at such speeds.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 99 , Issue 984 , April 1995, pp. 161 - 163
Copyright
Copyright © Royal Aeronautical Society 1995 

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References

1. Sanderson, S.R. and Simmons, J.M. Drag Balance for Hypervelocity Impulse Facilities, AIAA J, Dec 1991, 29, pp 2185–2191.Google Scholar
2. Simmons, J.M., Daniel, W.D., Mee, D.J., and Tuttle, S.L. Force Measurement in Hypervelocity Impulse Facilities, In: New Trends in Instrumentation for Hypersonic Research (Ed. Boutier, A.), Kluwer Academic Publishers, Amsterdam, 1993, pp 285–294.Google Scholar
3. Porter, L.M., Mee, D.J., and Simmons, J.M. Measuring the Effect on Drag Produced by Nose Bluntness on a Cone in Hypervelocity Flow, In: Proc. 11th Australasian Fluid Mechanics Conference (Eds Davis, M. and Walker, G.), University of Tasmania, Hobart, Australia, 14–18 December, 1992, pp 287–290.Google Scholar
4. Paull, A., Stalker, R.J. and Mee, D.J. Thrust Measurements of a Complete Axisymmetric Scramjet in an Impulse Facility, AIAA paper no. 93–5168. AIAA/DGLR Fifth International Aerospace Planes and Hypersonics Technologies Conference, Munich, Germany, 30 Nov-3 Dec 1993.Google Scholar
5. Lordi, J.A., Mates, R.E. and Moselle, J.R. Computer Program for Numerical Solution of Non-equilibrium Expansion of Reacting Gas Mixtures, NASA CR-472, 1966.Google Scholar