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Heat transfer and flow behind a step in high enthalpy superorbital flow

Published online by Cambridge University Press:  04 July 2016

M. J. Hayne ,
D. J. Mee ,
R. G. Morgan ,
S. L. Gai  and
T. J. Mclntyre
M. J. Hayne
Affiliation:
Centre for Hypersonics, Department of Mechanical Engineering, University of Queensland, Brisbane, Australia
D. J. Mee
Affiliation:
Centre for Hypersonics, Department of Mechanical Engineering, University of Queensland, Brisbane, Australia
R. G. Morgan
Affiliation:
Centre for Hypersonics, Department of Mechanical Engineering, University of Queensland, Brisbane, Australia
S. L. Gai
Affiliation:
School of Aerospace and Mechanical Engineering, University College, UNSW@ADFA, Canberra, Australia
T. J. Mclntyre
Affiliation:
Centre for Hypersonics, Department of Physics, University of Queensland, Brisbane, Australia
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Abstract

Heat transfer levels have been investigated behind a rearward-facing step in a superorbital expansion tube. The heat transfer was measured along a flat plate and behind 2 and 3mm steps with the same length to step height ratio. Results were obtained with air as the test gas at speeds of 6·76kms-1 and 9·60kms-1 corresponding to stagnation enthalpies of 26MJ/kg and 48MJ/kg respectively. A laminar boundary layer was established on the flat plate and measured heat transfer levels were consistent with classical empirical correlations. In the case of flow behind a step, the measurements showed a gradual rise in heat transfer from the rear of the step to a plateau several step heights downstream for both flow conditions. Reattachment distance was estimated to be approximately 1·6 step heights downstream of the 2mm step at the low enthalpy condition through the use of flow visualisation.

Type
Research Article
Information
The Aeronautical Journal , Volume 107 , Issue 1073 , July 2003 , pp. 435 - 442
Copyright
Copyright © Royal Aeronautical Society 2003 

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