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Supersonic Flow Past a Wedge with a Flame at its Apex

Published online by Cambridge University Press:  07 June 2016

R. Foster  and
J. F. Clarke
R. Foster
Affiliation:
College of Aeronautics, Cranfield
J. F. Clarke
Affiliation:
College of Aeronautics, Cranfield
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Summary

The wholly supersonic flow past a two-dimensional wedge is analysed on the assumption that release of chemical energy into the stream can be accomplished across a thin discontinuous plane flame front attached to the apex. Forces experienced by the wedge are calculated and representative flow patterns exhibited. Some typical interactions between the flame and shocks or centred simple waves are discussed, with emphasis on the use of pressure-flow-deflection diagrams to obtain results.

Type
Research Article
Information
Aeronautical Quarterly , Volume 19 , Issue 1 , February 1968 , pp. 80 - 90
Copyright
Copyright © Royal Aeronautical Society. 1968

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References

1. Rubins, P. M. and Rhodes, R. P. Jr. Shock induced combustion with oblique shocks. AIAA-ASME Hypersonic Ramjet Conference. Naval Ordnance Laboratory, White Oak, Md. AIAA Preprint 63-117,1963.Google Scholar
2. Clarke, J. F. Some remarks on the treatment of fully supersonic flames as gasdynamical discontinuities. College of Aeronautics, Co A Report Aero 179, 1965.Google Scholar
3. Lomax, H. Two-dimensional, supersonic, linearised flow with heat addition. NASA Memo 1-10-59 A, 1959.Google Scholar
4. Oswatitsch, K. Propulsion through heating at supersonic speed. RAE Library Translation 811, 1959.Google Scholar
5. Oswatitsch, K. Thrust and drag with heat addition to a supersonic flow. RAE Library Translation 1161, 1967.Google Scholar
6. NACA Ames Research Staff. Equations, tables and charts for compressible airflow. NACA Report 1135,1953.Google Scholar
7. Foster, R. Heat addition to a supersonic flow past a wedge: discontinuous flame sheet model. College of Aeronautics Thesis, October 1966.Google Scholar