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A numerical study of hypersonic laminar film cooling

Published online by Cambridge University Press:  04 July 2016

X. Yang ,
K. J. Badcock  and
B. E. Richards
X. Yang
Affiliation:
Department of Aerospace Engineering, University of Glasgow, UK
K. J. Badcock
Affiliation:
Department of Aerospace Engineering, University of Glasgow, UK
B. E. Richards
Affiliation:
Department of Aerospace Engineering, University of Glasgow, UK
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Abstract

A computational study has been performed to investigate the effectiveness of film cooling in hypersonic laminar flows. Both the primary and the coolant flow are air. First, three different primary flow conditions are used for validation. A uniform boundary condition at the slot exit is found to give unrealistic predictions of the heat transfer rate, whilst a boundary condition involving extended coolant inlet gives improvement. Then five coolant injection rates and three slot heights are examined. It is confirmed that increasing the coolant injection rate can increase the film cooling effectiveness for laminar cases. But slot height does not play an important role under the flow conditions in this study. The computational results are compared with the experimental results and good agreement is achieved.

Type
Research Article
Information
The Aeronautical Journal , Volume 107 , Issue 1074: University of Glasgow 50th year anniversary special , August 2003 , pp. 479 - 486
Copyright
Copyright © Royal Aeronautical Society 2003 

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