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Centre-Body Nozzles for Supersonic Transport Aircraft

Published online by Cambridge University Press:  04 July 2016

M. V. Herbert
M. V. Herbert*
Affiliation:
National Gas Turbine Establishment
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Summary

In a supersonic transport aircraft, the propelling nozzle is required to operate at high efficiency over a wide range of conditions — typically a five to ten-fold variation of exhaust pressure ratio. This paper offers some discussion around the problems of geometry which such requirements entail, and explains the reasons for which a nozzle of centre-body form with parallel outer shroud appears an attractive solution. In support of the claims for this arrangement of nozzle, test data are presented from both single and twin models under representative conditions of external flow. (The tests were made at the National Gas Turbine Establishment between 1960 and 1965.)

Type
Research Article
Information
The Aeronautical Journal , Volume 71 , Issue 673 , January 1967 , pp. 14 - 22
Copyright
Copyright © Royal Aeronautical Society 1967

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References

1.Lewis, W. G. E.Propelling Nozzle Research. Journal of the Royal Aeronautical Society, Vol. 68. No. 647, November 1964.Google Scholar
2.Migdal, D. and Horgan, J. J. Thrust Nozzles for Supersonic Transport Aircraft. ASME Paper 63-AHGT-73, 1963.Google Scholar
3.Herbert, M. V., Martlew, D. L. and Pinker, R. A. The Design-Point Performance of Model Internal- Expansion Propelling Nozzles with Area Ratios up to 4. ARC R & M 3477. December 1963.Google Scholar
4.Herbert, M. V. and Herd, R. J. Boundary-Layer Separation in Supersonic Propelling Nozzles. ARC R & M 3421, 1965.Google Scholar
5.Stratford, B. S. and Beavers, G. S. The Calculation of the Compressible Turbulent Boundary Layer in an Arbitrary Pressure Gradient—a Correlation of Certain Previous Methods. ARC R & M 3207, 1961.Google Scholar
6.Silvester, M. E. Unpublished work at Rolls-Royce Ltd.Google Scholar