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Circumferential Asymmetry in Axial Flow Compressors
Published online by Cambridge University Press: 04 July 2016
Extract
In this paper we are restricting our attention to those cases of circumferential inlet distortion where the distortion of the velocity profile is too large to be described as a small perturbation. Thus any theory describing the flow must use a mathematical model which is non-linear.
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- Copyright © Royal Aeronautical Society 1966
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