DC Field | Value | Language |
---|---|---|
dc.contributor.author | 박영민 | ko |
dc.contributor.author | 권오준 | ko |
dc.date.accessioned | 2013-03-02T23:58:03Z | - |
dc.date.available | 2013-03-02T23:58:03Z | - |
dc.date.created | 2012-02-06 | - |
dc.date.created | 2012-02-06 | - |
dc.date.issued | 2000-06 | - |
dc.identifier.citation | 한국항공우주학회지, v.28, no.4, pp.27 - 34 | - |
dc.identifier.issn | 1225-1348 | - |
dc.identifier.uri | http://hdl.handle.net/10203/76135 | - |
dc.description.abstract | Three-dimensional computations are performed for steady and unsteady transonic flows over a F-5 wing using a parallel implicit solver. The numerical scheme is based on a cell-centered finite-volume method with implicit Gauss-Seidel time integration and Roe`s flux-difference splitting. For parallel computation, local sub-domains are decomposed using MeTis library considering the balance of the number of cells. Parallel implementation is made using MPI library. Steady computation of a F-5 wing is performed to validate the capability of parallel computation. A case of an oscillating F-5 wing is also compared with experimental data for the validation of time accurate computations. | - |
dc.language | Korean | - |
dc.publisher | 한국항공우주학회 | - |
dc.title | 병렬화된 비정렬 내재적 기법을 이용한 진동하는 3차원 날개 주위의 비점성 유동 계산 | - |
dc.title.alternative | Calculation of Inviscid Flows over an Oscillating 3-D Wing Using an Unstructured Implicit Parallel Solver | - |
dc.type | Article | - |
dc.type.rims | ART | - |
dc.citation.volume | 28 | - |
dc.citation.issue | 4 | - |
dc.citation.beginningpage | 27 | - |
dc.citation.endingpage | 34 | - |
dc.citation.publicationname | 한국항공우주학회지 | - |
dc.contributor.localauthor | 권오준 | - |
dc.contributor.nonIdAuthor | 박영민 | - |
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