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Some Experiments on Two-Stream Propelling Nozzles for Supersonic Aircraft

Published online by Cambridge University Press:  04 July 2016

W. G. E. Lewis  and
F. W. Armstrong
W. G. E. Lewis
Affiliation:
National Gas Turbine Establishment., Pyestock, Hampshire
F. W. Armstrong
Affiliation:
National Gas Turbine Establishment., Pyestock, Hampshire
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Extract

The achievement of high propelling nozzle performance in supersonic flight is vital to the success of any aircraft designed to cruise supersonically for prolonged periods. For such projects, the payload fraction is small compared with subsonic aircraft, and the ratio of gross to net thrust is high. As a result, the penalty in range/payload performance for a shortfall in nozzle gross thrust efficiency is inevitably severe.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 75 , Issue 729 , September 1971 , pp. 648 - 654
Copyright
Copyright © Royal Aeronautical Society 1971 

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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. Taylor, J. B. (G.E.C. Cincinnati), Inlet duct-engine exhaust nozzle airflow matching for the supersonic transport, AIAA Paper No 67-574, October 1967.Google Scholar
3. Hardy, M. J. Theoretical study of an aerodynamic supersonic nozzle, Agardograph 103, October 1965.Google Scholar