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AERO-THERMAL PERFORMANCE OF A COOLED WINGLET AT ENGINE REPRESENTATIVE MACH AND REYNOLDS NUMBERS

Abstract:

This paper presents an experimental investigation of the aero-thermal performance of a cooled winglet tip, under transonic conditions (exit Mach number of 1.0, and an exit Reynolds number of 1.27×106, based on axial chord). Spatiallyresolved 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 calibrated...

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Publication status:
Published

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Publisher copy:
10.1115/GT2011-45610

Authors


O'Dowd, DO More by this author
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Institution:
University of Oxford
Department:
Oxford, MPLS, Engineering Science
Cheong, BCY More by this author
Tibbott, I More by this author
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Journal:
PROCEEDINGS OF THE ASME TURBO EXPO 2011, VOL 5, PTS A AND B
Volume:
5
Issue:
PARTS A AND B
Pages:
1235-1246
Publication date:
2012
DOI:
URN:
uuid:bff62a87-f76a-4904-a25f-c9ec1ee4cc46
Source identifiers:
351262
Local pid:
pubs:351262
Language:
English

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