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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

D. R. Topham
D. R. Topham*
Affiliation:
Advanced Projects Group, Hawker Siddeley Aviation Ltd.
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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.

Information

Type
Technical Notes
Information
The Aeronautical Journal , Volume 69 , Issue 649 , January 1965 , pp. 49 - 52
Copyright
Copyright © Royal Aeronautical Society 1965

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