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Transition of compressible high enthalpy boundary layer flow over a flat plate

Published online by Cambridge University Press:  04 July 2016

Y. He  and
R. G. Morgan
Y. He
Affiliation:
Department of Mechanical Engineering, University of Queensland, Australia
R. G. Morgan
Affiliation:
Department of Mechanical Engineering, University of Queensland, Australia
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Abstract

This paper presents the results of an experimental investigation into the characteristics of boundary layer transition to turbulence in hypervelocity air flows. A series of experiments was conducted using a flat plate model, equipped with static pressure and thin film heat transfer transducers, in a free piston shock tunnel. Transition was observed in the stagnation enthalpy range of 2·35 to 19·2 MJ/kg. The transition Reynolds number correlates well with the unit Reynolds number through a simple empirical relation. The influences of Mach number, pressure and wall cooling are examined. The measured heat transfer rates in laminar and turbulent regions are compared with empirical predictions. Freestream disturbances of the test flow were also measured and analysed.

Type
Research Article
Information
The Aeronautical Journal , Volume 98 , Issue 972 , February 1994 , pp. 25 - 34
Copyright
Copyright © Royal Aeronautical Society 1994 

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Footnotes

*

Currently at Department of Aerospace and Mechanical Engineering, University College, University of New South Wales, Australia.

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