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Some Comments “On The Effect of Shock-Induced Turbulent Separation on the Shock-Wave Position in a Nozzle”
Published online by Cambridge University Press: 04 July 2016
Extract
In Ref. 1, Professor D. W. Holder describes a very interesting experiment pertaining to shock wave position and boundary layer separation in supersonic nozzles at low Mach numbers (M ⩽ 1·4). A closer examination of this experiment indicates that the results may only be applicable in the Mach number range of M < 1·48, not in the range of M> 1·48.
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- Copyright © Royal Aeronautical Society 1962
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