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dc.contributor.advisorLittle, Jesse C.
dc.contributor.authorCastro Maldonado, Jorge Alberto
dc.creatorCastro Maldonado, Jorge Alberto
dc.date.accessioned2021-07-22T21:10:40Z
dc.date.available2021-06-22T03:11:24Z
dc.date.available2021-07-22T21:10:40Z
dc.date.issued2021
dc.identifier.citationCastro Maldonado, Jorge Alberto. (2021). Flow Structure and Heat Transfer Characterization of a Blunt-Fin-Induced Shock-Wave/Laminar Boundary-Layer Interaction (Master's thesis, University of Arizona, Tucson, USA).
dc.identifier.urihttp://hdl.handle.net/10150/660128.1
dc.identifier.urihttp://hdl.handle.net/10150/660128
dc.description.abstractAn experimental investigation of a blunt-fin-induced shock-wave/laminar boundary-layer interaction (SBLI) has been conducted at a nominal Mach number of 4.The experimental data is supplemented by computational results from Reynolds-averaged Navier Stokes computations provided by Raytheon Missiles & Defense.Two blunt fins with a leading-edge diameter of 9.525 mm (3/8”) and sweep angles of 0 and 45 degrees were tested on a flat plate with unit Reynolds number 4.3×10^6 m−1 (Re_x= 2.7×10^5). The unswept fin produces significant separation extending x/D ≈ −5.5 upstream of the fin leading edge. Mach number contours indicate two horseshoe vortices wrapping around the unswept fin base. The swept fin SBLI features are subdued in comparison, but qualitatively similar, with evidence of horseshoe vortices also present. Temperature sensitive paint (TSP) was employed to investigate the near-wall flow structure and estimate surface heat flux. Prominent features include various reattachment lines associated with vortices in the separated region, as well as shock-shock interactions and shear-layer impingement on the fin leading edge. Increasing the sweep angle altered the flow topology considerably, including the location and magnitude of maximum heat flux. The surface distribution of Stanton numbers are derived, demonstrating complex interactions with a rich set of flow physics to be investigated in future work. Amongst other findings, the influence of sweep has a moderate impact on peak heat transfers, with Stanton numbers reaching 0.022 and 0.035 for the swept and unswept fins respectively.en_US
dc.language.isoenen_US
dc.publisherThe University of Arizona.en_US
dc.rightsCopyright © is held by the author. Digital access to this material is made possible by the University Libraries, University of Arizona. Further transmission, reproduction, presentation (such as public display or performance) of protected items is prohibited except with permission of the author.en_US
dc.rights.urihttp://rightsstatements.org/vocab/InC/1.0/
dc.subjectBlunt finen_US
dc.subjectFlow structureen_US
dc.subjectHeat transferen_US
dc.subjectLaminaren_US
dc.subjectSBLIen_US
dc.subjectShock shock interactionen_US
dc.titleFlow Structure and Heat Transfer Characterization of a Blunt-Fin-Induced Shock-Wave/Laminar Boundary-Layer Interactionen_US
dc.typetexten_US
dc.typeElectronic Thesisen_US
thesis.degree.grantorUniversity of Arizonaen_US
thesis.degree.levelmastersen_US
dc.contributor.committeememberCraig, Stuart A.
dc.contributor.committeememberWernz, Stefan
thesis.degree.disciplineGraduate Collegeen_US
thesis.degree.disciplineAerospace Engineeringen_US
thesis.degree.nameM.S.en_US
dc.description.noteRevised version with modified coding in appendices approved by Graduate College 16-July-2021; revised PDF dissertation file added to UA Campus Repository 22-July-2021.en_US
refterms.dateFOA2021-06-22T03:11:25Z


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