Please use this identifier to cite or link to this item:
https://hdl.handle.net/20.500.11851/7556
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DC Field | Value | Language |
---|---|---|
dc.contributor.author | Kaynak, Ünver | - |
dc.date.accessioned | 2021-09-11T15:57:49Z | - |
dc.date.available | 2021-09-11T15:57:49Z | - |
dc.date.issued | 2012 | en_US |
dc.identifier.issn | 0954-4100 | - |
dc.identifier.issn | 2041-3025 | - |
dc.identifier.uri | https://doi.org/10.1177/0954410011416187 | - |
dc.identifier.uri | https://hdl.handle.net/20.500.11851/7556 | - |
dc.description.abstract | The effect of compressibility on supersonic boundary layer transition is simulated by modifying a standard gamma-Re-theta t correlation-based transition model under two-dimensional (2D) approximation. First, the gamma-Re-theta t model's empirical correlations derived for low Mach numbers are validated against some well-known subsonic flat plate experiments. Second, the same empirical correlations are tested against a direct numerical simulation (DNS) dataset closely approximating a supersonic flat plate experiment at M = 2.25. Finally, the present empirical correlations are extended for supersonic speeds using a known compressibility correlation. For this, the free stream turbulence level is assumed to remain constant and the free stream velocity is increased up to a supersonic speed of Mach 2.7 using adiabatic wall conditions. Numerical results show that the modified gamma-Re-theta t transition model is capable of predicting the downstream movement of the transition onset location in good agreement with the linear theory, experiments, and DNS data up to Mach 2.25. The length of the transition region is observed to grow with higher Mach numbers, and destabilizing effect of compressibility after Mach 2.0 is also predicted, in a limited sense, under the 2D approximation. | en_US |
dc.language.iso | en | en_US |
dc.publisher | Sage Publications Ltd | en_US |
dc.relation.ispartof | Proceedings of The Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering | en_US |
dc.rights | info:eu-repo/semantics/closedAccess | en_US |
dc.subject | correlation-based transition modelling | en_US |
dc.subject | transition onset location | en_US |
dc.subject | transition length | en_US |
dc.subject | transition point momentum thickness | en_US |
dc.subject | compressibility correlation | en_US |
dc.subject | linear stability theory | en_US |
dc.subject | Reynolds-averaged Navier-Stokes | en_US |
dc.subject | direct/large eddy simulation | en_US |
dc.subject | shear stress transport | en_US |
dc.subject | k-omega SST transition/turbulence model | en_US |
dc.title | Supersonic Boundary-Layer Transition Prediction Under the Effect of Compressibility Using a Correlation-Based Model | en_US |
dc.type | Article | en_US |
dc.department | Faculties, Faculty of Engineering, Department of Mechanical Engineering | en_US |
dc.department | Fakülteler, Mühendislik Fakültesi, Makine Mühendisliği Bölümü | tr_TR |
dc.identifier.volume | 226 | en_US |
dc.identifier.issue | G7 | en_US |
dc.identifier.startpage | 722 | en_US |
dc.identifier.endpage | 739 | en_US |
dc.identifier.wos | WOS:000305567900001 | en_US |
dc.institutionauthor | Kaynak, Ünver | - |
dc.identifier.doi | 10.1177/0954410011416187 | - |
dc.relation.publicationcategory | Makale - Uluslararası Hakemli Dergi - Kurum Öğretim Elemanı | en_US |
dc.identifier.scopusquality | Q2 | - |
item.openairetype | Article | - |
item.languageiso639-1 | en | - |
item.grantfulltext | none | - |
item.fulltext | No Fulltext | - |
item.openairecristype | http://purl.org/coar/resource_type/c_18cf | - |
item.cerifentitytype | Publications | - |
crisitem.author.dept | 02.7. Department of Mechanical Engineering | - |
Appears in Collections: | Makine Mühendisliği Bölümü / Department of Mechanical Engineering WoS İndeksli Yayınlar Koleksiyonu / WoS Indexed Publications Collection |
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