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Derivation of the “Prandtl-Meyer” Expansion Solution from the Linear Approximation
Published online by Cambridge University Press: 28 July 2016
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Each small stage of the expansion starts with a uniform supersonic stream and finishes with a similar stream accelerated, expanded and turned through a small angle. We are therefore justified in applying to each stage the linear (Ackeret) approximation for small departures from uniform flow, according to which
where U = air velocity
M = Mach number
α = inclination of flow.
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- Copyright © Royal Aeronautical Society 1956
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