DC Field | Value | Language |
---|---|---|
dc.contributor.author | 최성욱 | ko |
dc.contributor.author | 장근식 | ko |
dc.contributor.author | 김인선 | ko |
dc.date.accessioned | 2010-09-10T02:25:39Z | - |
dc.date.available | 2010-09-10T02:25:39Z | - |
dc.date.created | 2012-02-06 | - |
dc.date.created | 2012-02-06 | - |
dc.date.issued | 2000-09 | - |
dc.identifier.citation | 한국전산유체공학회지, pp.9 - 19 | - |
dc.identifier.issn | 1598-6071 | - |
dc.identifier.uri | http://hdl.handle.net/10203/19419 | - |
dc.description.abstract | Transient aerodynamic response of an airfoil to a moving plane-flap is numerically investigated using the two-dimensional Euler equations with conservative Chimera grid method. A body moving relative to a stationary grid is treated by an overset grid bounded by a 'Dynamic Domain Dividing Line' which has an advantage for constructing a well-defined hole-cutting boundary. A conservative Chimera grid method with the dynamic domain-dividing line technique is applied and validated by solving the flowfield around a circular cylinder moving supersonic speed. The unsteady and transient characteristics of the flow solver are also examined by computations of an oscillating airfoil and a ramp pitching airfoil respectively. The transient aerodynamic behavior of an airfoil with a moving plane-flap is analyzed for various flow conditions such as deflecting rate of flap and free stream Mach number. | - |
dc.language | Korean | - |
dc.language.iso | ko | en |
dc.publisher | 한국전산유체공학회 | - |
dc.title | 보존적 중첩격자기법을 이용한 동적 플랩의 천이적 공력거동에 관한 수치적 연구 | - |
dc.type | Article | - |
dc.identifier.alternativecitation | Journal of computational fluids engineering v.5 no.2 pp.9-19 | en |
dc.type.rims | ART | - |
dc.citation.beginningpage | 9 | - |
dc.citation.endingpage | 19 | - |
dc.citation.publicationname | 한국전산유체공학회지 | - |
dc.embargo.liftdate | 9999-12-31 | - |
dc.embargo.terms | 9999-12-31 | - |
dc.contributor.localauthor | 장근식 | - |
dc.contributor.nonIdAuthor | 최성욱 | - |
dc.contributor.nonIdAuthor | 김인선 | - |
Items in DSpace are protected by copyright, with all rights reserved, unless otherwise indicated.