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On the Effect of Shock-Induced Turbulent Separation on the Shock-Wave Position in a Nozzle

Published online by Cambridge University Press:  04 July 2016

D. W. Holder
D. W. Holder*
Affiliation:
Aerodynamics Division, National Physical Laboratory now Professor and, Head of Dept. of Engineering Science, Engineering Laboratory, Oxford
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Abstract

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Type
Technical Notes
Information
The Aeronautical Journal , Volume 65 , Issue 609 , September 1961 , pp. 633 - 634
Copyright
Copyright © Royal Aeronautical Society 1961

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References

1.Holder, D. W., Pearcey, H. H. and Gadd, G. E. (1954). The Interaction Between Shock Waves and Boundary Layers. A.R.C. Current Paper 180, 1954.Google Scholar
2.Pearcey, H. H. (1955). Some Effects of Shock-induced Separation of Turbulent Boundary Layers in Transonic Flow Past Aerofoils. Proc. N.P.L. Symposium on Boundary Layer Effects in Aerodynamics 1955.Google Scholar
3.Holder, D. W. and Cash, R. F. (1957). Experiments with a Two-dimensional Aerofoil Designed to be Free from Turbulent Boundary-Layer Separation at small Angles of Incidence for all Mach Numbers. A.R.C. R. & M. 3100, 1957.Google Scholar
4.Sinnott, C. S. and Osborne, J. Review and Extension of Transonic Aerofoil Theory. A.R.C. R. & M. 3156, UnpublishedGoogle Scholar
5.Pearcey, H. H. (1960). Aerodynamic Design of Section Shapes for Swept Wings. Second International Conference in the Aeronautical Sciences, Zurich, 1960. Pergamon Press 1961.Google Scholar
6.Pearcey, H. H. (1961). Shock-inclined Separation, and its Prevention by Design and Boundary-Layer Control. Boundary- layer and Flow Control. Lachmann, G. V., Ed. Pergamon, 1961.Google Scholar