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Some Comments “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

I. I. Glass  and
G. K. Korbacher
I. I. Glass
Affiliation:
Institute of Aerophysics, University of Toronto, Canada
G. K. Korbacher
Affiliation:
Institute of Aerophysics, University of Toronto, Canada
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Extract

In Ref. 1, Professor D. W. Holder describes a very interesting experiment pertaining to shock wave position and boundary layer separation in supersonic nozzles at low Mach numbers (M ⩽ 1·4). A closer examination of this experiment indicates that the results may only be applicable in the Mach number range of M < 1·48, not in the range of M> 1·48.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 66 , Issue 619 , July 1962 , pp. 454 - 455
Copyright
Copyright © Royal Aeronautical Society 1962

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References

1.Holder, D. W. (1961). On the Effect of Shock-Induced Turbulent Separation on the Shock-Wave Position in a Nozzle. Journal of the Royal Aeronautical Society, Vol. 65, Sept. 1961.CrossRefGoogle Scholar
2.Liepmann, H. W. and Roshko, A. (1957). Elements of Gas-dynamics. John Wiley and Sons, New York, 1957.Google Scholar
3.Shapiro, A. (1953). The Dynamics and Thermodynamics of Compressible Fluid Flow. Ronald Press, New York, 1953.Google Scholar
4.Emmons, H. W. (Editor) (1958). Fundamentals of Gas Dynamics, Princeton University Press, 1958.CrossRefGoogle Scholar
5.Chapman, D. R., Kuehn, D. M. and Larson, H. K. (1958). Investigation of Separated Flows in Supersonic and Subsonic Streams with Emphasis on the Effect of Transition. NACA Report 1356, 1958.Google Scholar