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The Compressible Discharge Coefficient of a Borda Pipe and other Nozzles

Published online by Cambridge University Press:  04 July 2016

T. H. Frost
T. H. Frost*
Affiliation:
Research Department, Aero Engine Division, Rolls-Royce Ltd.
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Extract

Bragg, in ref. 1, gives a theoretical treatment for the variation of the discharge coefficient in compressible flow of any shaped nozzle with applied pressure ratio given one set of values. This shows that the discharge coefficient of any nozzle with a value less than unity at a pressure ratio approaching unity, rises continuously as the pressure ratio increases and reaches the maximum at a pressure ratio of infinity (zero back pressure). This is based on the assumption that the flow conditions at the Vena contracta are uniform and at unity Mach number once the applied pressure ratio is equal to/ or above the critical (sonic) value.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 68 , Issue 641 , May 1964 , pp. 346 - 349
Copyright
Copyright © Royal Aeronautical Society 1964

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References

1.Bragg, S. L.Effect of Compressibility on the Discharge Coefficient of Orifices and Convergent Nozzles. Journal Mechanical Engineering Sciences, Vol. 2, No. 1, 1960.CrossRefGoogle Scholar
2.Smith, S. F. The Thrust of Convergent Nozzles. (Unpublished Rolls-Royce Aero Div. Technical Report.)Google Scholar