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Scramjet thrust measurement in a shock tunnel

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 a fully integrated scramjet configuration produced net thrust. The experiments not only showed that impulse facilities can be used for assessing thrust performance, but also were a demonstration of the application of a new technique(1) to the measurement of thrust on scramjet configurations in shock tunnels. These two developments are of significance because scramjets are expected to operate at speeds well in excess of 2 km/s, and shock tunnels offer a means of generating high Mach number 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

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