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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
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.
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- Copyright © Royal Aeronautical Society 1975
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