DC Field | Value | Language |
---|---|---|
dc.contributor.author | Sohn, MH | - |
dc.contributor.author | Chang, JW | - |
dc.contributor.author | null | - |
dc.date.accessioned | 2016-04-01T03:32:53Z | - |
dc.date.available | 2016-04-01T03:32:53Z | - |
dc.date.issued | 2010-01 | - |
dc.identifier.citation | AEROSPACE SCIENCE AND TECHNOLOGY | - |
dc.identifier.citation | v.14 | - |
dc.identifier.citation | no.1 | - |
dc.identifier.citation | pp.11-18 | - |
dc.identifier.issn | 1270-9638 | - |
dc.identifier.other | 2010-OAK-0000020054 | - |
dc.identifier.uri | https://oasis.postech.ac.kr/handle/2014.oak/26592 | - |
dc.description.abstract | The effect of the presence of a centerbody on the vortex flow of a uniquely-shaped double-delta wing was experimentally investigated through simultaneous off-surface flow visualization and wing-surface pressure measurements. The uniquely-shape double-delta wing was formed by attaching a leading edge extension (LEX) to the apex portion of a 65-deg sweep delta wing with sharp edges. The flow Reynolds number was 1.82 x 10(5) for the off-surface flow visualization, 1.76 x 10(6) for the wing-surface pressure measurement. Visualization results show that the presence of a centerbody under the lower surface of the double-delta wing model slightly advanced coiling interaction of the wing and LEX vortices at the downstream chord positions, at least for the selected angle of attack of 24-deg. Quantitative analysis of wing-surface pressure measurements revealed the effects of the presence of a centerbody to be prominent for the cases with higher angles of attack and sideslip angles. Up to angle of attack alpha = 24-deg, the presence of the centerbody had a small influence on the suction pressure distribution on the wing upper surface, even at the large sideslip angle of -20-deg. However, at higher angles of attack of 28-deg and 32-deg, the presence of the centerbody caused a decrease in the magnitude of suction pressure distributions on the wing's upper surface, and the difference of the suction pressure distribution between the two configurations was not negligible at non-zero sideslip angles. (C) 2009 Elsevier Masson SAS. All rights reserved. | - |
dc.description.statementofresponsibility | X | - |
dc.publisher | ELSEVIER FRANCE-EDITIONS SCIENTIFIQUES MEDICALES ELSEVIER | - |
dc.subject | Double-delta wing | - |
dc.subject | Vortex flow | - |
dc.subject | Centerbody | - |
dc.subject | Off-surface flow visualization | - |
dc.subject | Wing-surface pressure measurement | - |
dc.subject | FUSELAGE GEOMETRY | - |
dc.subject | BREAKDOWN | - |
dc.subject | VISUALIZATION | - |
dc.subject | AERODYNAMICS | - |
dc.title | Effect of a centerbody on the vortex flow of a double-delta wing with leading edge extension | - |
dc.type | Article | - |
dc.identifier.doi | 10.1016/J.AST.2009.11.004 | - |
dc.author.google | Sohn, MH | - |
dc.author.google | Chang, JW | - |
dc.relation.volume | 14 | - |
dc.relation.issue | 1 | - |
dc.relation.startpage | 11 | - |
dc.relation.lastpage | 18 | - |
dc.publisher.location | FR | - |
dc.relation.journal | AEROSPACE SCIENCE AND TECHNOLOGY | - |
dc.relation.index | SCI급, SCOPUS 등재논문 | - |
dc.relation.sci | SCI | - |
dc.collections.name | Journal Papers | - |
dc.type.docType | Article | - |
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