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Direct numerical simulation of a swept-wing boundary layer with an array of discrete roughness elements

Abstract:

Direct numerical simulations of crossflow-induced boundary layer transition are performed for a 45-degree swept wing with an array of discrete roughness elements placed near the leading edge, at a chord Reynolds number of 2.4 million. A large part of the wing upper surface in the chordwise direction (but with only less than two-percent chord in the spanwise direction) is resolved to simulate the growth and breakdown of crossflow vortices on the wing. The procedures, initial results and some d...

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Authors


Nishino, T More by this author
Shariff, K More by this author
Volume:
18
Pages:
289-294
Publication date:
2010
DOI:
ISSN:
1875-3507
URN:
uuid:22baad54-67ef-447a-beb1-227f23dabe6b
Source identifiers:
332130
Local pid:
pubs:332130
ISBN:
9789048137220

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