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The Effect of Shock Waves on the Isentropic Efficiency of Convergent— Divergent Nozzles

Published online by Cambridge University Press:  04 July 2016

B. W. Martin  and
F. J. Bayley
B. W. Martin
Affiliation:
Department of Mechanical and Marine Engineering , King's College, University of Durham
F. J. Bayley
Affiliation:
Department of Mechanical and Marine Engineering , King's College, University of Durham
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Extract

Now a Days, the phenomenon is well known of the plane normal shock waves set up in the divergent section of a convergent-divergent nozzle, and the oblique shocks which occur in the resultant jet downstream of the nozzle exit when operating under overall pressure ratios less than the design value. Stodola was among the first to demonstrate experimentally the effect on the flow within the nozzle of increasing the back pressure above the design value, and work by Schmidt, Martin) and others, has been concerned with the theoretical changes in pressure, temperature, density and Mach number across a normal shock wave whose position varies along the nozzle axis. The effect of working substance on these changes, which is taken into account by the ratio of specific heats, has also been investigated.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 62 , Issue 569 , May 1958 , pp. 377 - 382
Copyright
Copyright © Royal Aeronautical Society 1958

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References

1.Stodola, A. (1924). Dampf—U. Gasturbinen, 6th Edition, Springer, Berlin, p. 69, 1924.Google Scholar
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3.Martin, B. W. (1953). Normal Shock Wave Phenomena in a Convergent-Divergent Nozzle. Journal of the Royal Aeronautical Society, Vol. 57, p. 455, July 1953.Google Scholar
4.Cohen, H. and Rogers, G. F. C. (1951). Gas Turbine Theory. Longmans, Green, and Company, 1951.Google Scholar
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