DC Field | Value | Language |
---|---|---|
dc.contributor.author | 임동균 | ko |
dc.contributor.author | 최성임 | ko |
dc.contributor.author | 김유진 | ko |
dc.contributor.author | 권장혁 | ko |
dc.contributor.author | 박수형 | ko |
dc.date.accessioned | 2013-03-12T21:15:23Z | - |
dc.date.available | 2013-03-12T21:15:23Z | - |
dc.date.created | 2013-01-07 | - |
dc.date.created | 2013-01-07 | - |
dc.date.issued | 2012-03 | - |
dc.identifier.citation | 한국전산유체공학회지, v.17, no.1, pp.70 - 77 | - |
dc.identifier.issn | 1598-6071 | - |
dc.identifier.uri | http://hdl.handle.net/10203/103530 | - |
dc.description.abstract | In this paper, diagonal implicit harmonic balance method with overset grid technique is applied to analyze helicopter rotor blade flow in hover and forward flight condition. The chimera grid need interpolation time with sub-grid and background grid in moving problem such as forward flight on every time step. Present method is available enough to reduce the grid module interpolation time. In order to demonstrate present method, Caradonna & Tung's and AH-1G rotor blades are used and the results are compared to other researchers’ result and experimental data. | - |
dc.language | Korean | - |
dc.publisher | 한국전산유체공학회 | - |
dc.title | 중첩 격자 기법이 적용된 대각 내재적 조화균형법을 이용한 헬리콥터 로터 블레이드의 비정상 공력 해석 | - |
dc.title.alternative | UNSTEADY AERODYNAMIC ANALYSIS OF HELICOPTER ROTOR BLADES USING DIAGONAL IMPLICIT HARMONIC BALANCE METHOD | - |
dc.type | Article | - |
dc.type.rims | ART | - |
dc.citation.volume | 17 | - |
dc.citation.issue | 1 | - |
dc.citation.beginningpage | 70 | - |
dc.citation.endingpage | 77 | - |
dc.citation.publicationname | 한국전산유체공학회지 | - |
dc.identifier.kciid | ART001646338 | - |
dc.contributor.localauthor | 최성임 | - |
dc.contributor.localauthor | 권장혁 | - |
dc.contributor.nonIdAuthor | 임동균 | - |
dc.contributor.nonIdAuthor | 김유진 | - |
dc.contributor.nonIdAuthor | 박수형 | - |
dc.subject.keywordAuthor | 조화 균형법(Harmonic Balance Method) | - |
dc.subject.keywordAuthor | 헬리콥터 로터 유동 | - |
dc.subject.keywordAuthor | 중첩격자기법(Overset Method) | - |
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