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A Correlation of Leading Edge Transition and Heat Transfer on Swept Cylinders in Supersonic Flow
Published online by Cambridge University Press: 04 July 2016
Summary:—
It is shown that stagnation line heating rates for laminar, transitional and turbulent boundary layers measured on swept cylinders at supersonic speeds, can be correlated in terms of a Reynolds number based on the spanwise momentum thickness at the stagnation line.
A critical Reynolds number for transition along the stagnation line is determined and experimental results show evidence of transition up to M= 10.
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- Copyright © Royal Aeronautical Society 1965
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