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dc.contributor.authorStodůlka , Jiří
dc.contributor.authorŠafařík , Pavel
dc.date.accessioned2017-02-09T09:56:08Z
dc.date.available2017-02-09T09:56:08Z
dc.date.issued2015
dc.identifier.citationActa Polytechnica. 2015, vol. 55, no. 3, p. 193-198.
dc.identifier.issn1210-2709 (print)
dc.identifier.issn1805-2363 (online)
dc.identifier.urihttp://hdl.handle.net/10467/67198
dc.description.abstractTransonic flow past two cusped airfoils is numerically solved and achieved results are analyzed by means of flow behavior and oblique shocks formation.Regions around sharp trailing edges are studied in detail and parameters of shock waves are solved and compared using classical shock polar approach and verified by reduction parameters for symmetric configurations.en
dc.format.mimetypeapplication/pdf
dc.language.isoeng
dc.publisherČeské vysoké učení technické v Prazecs
dc.publisherCzech Technical University in Pragueen
dc.relation.ispartofseriesActa Polytechnica
dc.relation.urihttps://ojs.cvut.cz/ojs/index.php/ap/article/view/2297
dc.rightsCreative Commons Attribution 4.0 International Licenseen
dc.rights.urihttp://creativecommons.org/licenses/by/4.0/
dc.subjectoblique shocken
dc.subjectshock polaren
dc.subjecttrailing edgeen
dc.subjectcusped airfoilen
dc.subjecttransonic flowen
dc.subjectCFDen
dc.titleANALYSIS OF TRANSONIC FLOW PAST CUSPED AIRFOILS
dc.typearticleen
dc.date.updated2017-02-09T09:56:08Z
dc.identifier.doihttps://doi.org/10.14311/AP.2015.55.0193
dc.rights.accessopenAccess
dc.type.statusPeer-reviewed
dc.type.versionpublishedVersion


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Except where otherwise noted, this item's license is described as Creative Commons Attribution 4.0 International License