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DC poleHodnotaJazyk
dc.contributor.authorMusil, Josef
dc.contributor.authorPříhoda, Jaromír
dc.contributor.authorFürst, Jiří
dc.date.accessioned2022-01-13T06:55:45Z
dc.date.available2022-01-13T06:55:45Z
dc.date.issued2021
dc.identifier.citationApplied and Computational Mechanics. 2021, vol. 15, no. 2, p. 175-184.en
dc.identifier.issn1802-680X (Print)
dc.identifier.issn2336-1182 (Online)
dc.identifier.urihttp://hdl.handle.net/11025/46605
dc.format10 s.cs
dc.format.mimetypeapplication/pdf
dc.language.isoenen
dc.publisherUniversity of West Bohemiaen
dc.rights© University of West Bohemiaen
dc.subjectkaskáda čepele nadzvukové špičkycs
dc.subjectCFDcs
dc.subjectpřechodové modelovánícs
dc.titleNumerical simulations of the 2D supersonic flow through the tip-section turbine blade cascade with a flat profileen
dc.typečlánekcs
dc.typearticleen
dc.rights.accessopenAccessen
dc.type.versionpublishedVersionen
dc.description.abstract-translatedNumerical simulations of 2D compressible flow through the tip-section turbine blade cascade with a flat profile and the supersonic inlet were carried out by the OpenFOAM code using the Favre-averaged Navier-Stokes equations completed by the γ-Re_θt bypass transition model with the SST turbulence model. Predictions completed for nominal regimes were concentrated particularly on the effect of the shock-wave/boundary layer interaction on the transition to turbulence. Further, the link between the inlet Mach number and the inlet flow angle i.e. the so called unique incidence rule was studied. Obtained numerical results were compared with experimental data covering optical and pressure measurements.en
dc.subject.translatedsupersonic tip-section blade cascadeen
dc.subject.translatedCFDen
dc.subject.translatedtransition modellingen
dc.identifier.doihttps://doi.org/10.24132/acm.2021.621
dc.type.statusPeer-revieweden
Vyskytuje se v kolekcích:Volume 15, number 2 (2021)
Volume 15, number 2 (2021)

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