Please use this identifier to cite or link to this item: http://hdl.handle.net/10397/81372
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dc.contributorDepartment of Civil and Environmental Engineering-
dc.creatorGhalandari, M-
dc.creatorShamshirband, S-
dc.creatorMosavi, A-
dc.creatorChau, KW-
dc.date.accessioned2019-09-20T00:55:13Z-
dc.date.available2019-09-20T00:55:13Z-
dc.identifier.issn1994-2060-
dc.identifier.urihttp://hdl.handle.net/10397/81372-
dc.language.isoenen_US
dc.publisherTaylor & Francisen_US
dc.rights© 2019 The Author(s). Published by Informa UK Limited, trading as Taylor & Francis Groupen_US
dc.rightsThis is an Open Access article distributed under the terms of the Creative Commons Attribution License (http://creativecommons.org/licenses/by/4.0/), which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.en_US
dc.rightsThe following publication Mohammad Ghalandari, Shahaboddin Shamshirband, Amir Mosavi & Kwokwing Chau (2019) Flutter speed estimation using presented differential quadrature method formulation, Engineering Applications of Computational Fluid Mechanics, 13:1, 804-810 is available at https://dx.doi.org/10.1080/19942060.2019.1627676en_US
dc.subjectAero-elasticityen_US
dc.subjectSubsonic regimeen_US
dc.subjectDeferential quadrature method (DQM)en_US
dc.subjectTypical section beamen_US
dc.subjectAerodynamicen_US
dc.subjectWing designen_US
dc.subjectAirfoilen_US
dc.subjectComputational fluid dynamics (CFD)en_US
dc.subjectFlutter speed predictionen_US
dc.titleFlutter speed estimation using presented differential quadrature method formulationen_US
dc.typeJournal/Magazine Articleen_US
dc.identifier.spage804-
dc.identifier.epage810-
dc.identifier.volume13-
dc.identifier.issue1-
dc.identifier.doi10.1080/19942060.2019.1627676-
dcterms.abstractIn this paper the flutter behavior of a typical wing is investigated. The study is performed by presented Deferential Quadrature Method (DQM). The aerodynamic part adopted Wagner functions to model subsonic regime. Quasi steady and unsteady aerodynamics are considered to estimate the instability speed of the structure. Based on the presented model, a code is developed, for an arbitrary typical section beam. The obtained results validated the existing methods in the literature. The proposed method provides the advantage of finding the modes of oscillation and other dynamic parameters with less than 0.2% difference.-
dcterms.accessRightsopen accessen_US
dcterms.bibliographicCitationEngineering applications of computational fluid mechanics, 1 Jan. 2019, v. 13, no. 1, p. 804-810-
dcterms.isPartOfEngineering applications of computational fluid mechanics-
dcterms.issued2019-
dc.identifier.isiWOS:000477866000001-
dc.identifier.scopus2-s2.0-85069968273-
dc.identifier.eissn1997-003X-
dc.description.validate201909 bcrc-
dc.description.oaVersion of Recorden_US
dc.identifier.FolderNumberOA_Scopus/WOSen_US
dc.description.pubStatusPublisheden_US
dc.description.oaCategoryCCen_US
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