Hostname: page-component-78c5997874-xbtfd Total loading time: 0 Render date: 2024-11-20T03:58:42.314Z Has data issue: false hasContentIssue false
  • English
  • Français

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
Get access Rights & Permissions [Opens in a new window]

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.

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

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. 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