Assessment of Rotor Hover Performance Using a Node-Based Flow Solver

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dc.contributor.authorJung Mun-Seungko
dc.contributor.authorKwon Oh-Joonko
dc.contributor.authorKang Hee-Jungko
dc.date.accessioned2013-03-08T00:48:04Z-
dc.date.available2013-03-08T00:48:04Z-
dc.date.created2012-02-06-
dc.date.created2012-02-06-
dc.date.issued2007-11-
dc.identifier.citationINTERNATIONAL JOURNAL OF AERONAUTICAL AND SPACE SCIENCES , v.8, no.2, pp.44 - 53-
dc.identifier.issn2093-274X-
dc.identifier.urihttp://hdl.handle.net/10203/91638-
dc.description.abstractA three-dimensional viscous flow solver has been developed for the prediction of the aerodynamic performance of hovering helicopter rotor blades using unstructured hybrid meshes. The flow solver utilized a vertex-centered finite-volume scheme that is based on the Roes flux-difference splitting with an implicit Jacobi/Gauss-Seidel time integration. The eddy viscosity are estimated by the Spalart-Allmaras one-equation turbulence model. Calculations were performed at three operating conditions with varying tip Mach number and collective pitch setting for the Caradonna-Tung rotor in hover. Additional computations are made for the UH-60A rotor in hover. Reasonable agreements were obtained between the present results and the experiment in both blade loading and overall rotor performance. It was demonstrated that the present vertex-centered flow solver is an efficient and accurate tool for the assessment of rotor performance in hover.-
dc.languageEnglish-
dc.publisher한국항공우주학회-
dc.titleAssessment of Rotor Hover Performance Using a Node-Based Flow Solver-
dc.typeArticle-
dc.type.rimsART-
dc.citation.volume8-
dc.citation.issue2-
dc.citation.beginningpage44-
dc.citation.endingpage53-
dc.citation.publicationnameINTERNATIONAL JOURNAL OF AERONAUTICAL AND SPACE SCIENCES-
dc.contributor.localauthorKwon Oh-Joon-
dc.contributor.nonIdAuthorJung Mun-Seung-
dc.contributor.nonIdAuthorKang Hee-Jung-
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AE-Journal Papers(저널논문)
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