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Aerothermal Performance of a Cooled Winglet at Engine Representative Mach and Reynolds Numbers

Abstract:

This paper presents an experimental investigation of the aerothermal performance of a cooled winglet tip under transonic conditions (exit Mach number of 1.0, and an exit Reynolds number of 1.27 x 106, based on axial chord). Spatially resolved heat transfer data and film cooling effectiveness data are obtained using the transient infrared thermography technique in the Oxford High-Speed Linear Cascade test facility. Aerodynamic loss data are obtained by traversing a specially made and calibrate...

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Publication status:
Published

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Publisher copy:
10.1115/1.4006537

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Institution:
University of Oxford
Department:
Oxford, MPLS, Engineering Science
Role:
Author
Journal:
JOURNAL OF TURBOMACHINERY-TRANSACTIONS OF THE ASME
Volume:
135
Issue:
1
Pages:
011041-011041
Publication date:
2013-01-05
DOI:
EISSN:
1528-8900
ISSN:
0889-504X
URN:
uuid:07cc400e-a508-4646-b16a-caadc4b3e24d
Source identifiers:
360007
Local pid:
pubs:360007
Language:
English

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