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Calculation of Mach number from given turning angle in supersonic isentropic flow

Published online by Cambridge University Press:  04 July 2016

S. M. Fraser
S. M. Fraser*
Affiliation:
Department of Thermodynamics and Fluid Mechanics, University of Strathclyde
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Extract

In many design procedures for calculating supersonic isentropic flow the problem arises of calculating the change in Mach number which will occur due to a specified change in flow direction, e.g. considering simple Prandtl-Meyer corner flow, it is required to calculate the final Mach number M to which the initial sonic stream will be accelerated by turning through a specified angle v.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 79 , Issue 770 , February 1975 , pp. 95 - 96
Copyright
Copyright © Royal Aeronautical Society 1975 

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References

1. Probstein, R.F. Inversion of the Prandtl-Meyer relation for specific heat ratios of 5/3 and 5/4. J Aero Sci, Vol 24, pp 316–7, April 1957.Google Scholar
2. Houghton, E.L. and Brock, A.E. Tables for the compressible flow of dry air. Edward Arnold (Publishers) Limited, 1961.Google Scholar