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dc.contributor.authorMan, Sek Ong.
dc.creatorMan, Sek Ong.en_US
dc.date.accessioned2011-10-31T18:08:25Z
dc.date.available2011-10-31T18:08:25Z
dc.date.issued1993en_US
dc.identifier.urihttp://hdl.handle.net/10150/186411
dc.description.abstractNumerical experiments are conducted to simulate airfoils pitching up at constant rates into the dynamic stall regime using the Beam and Warming algorithm for compressible Navier-Stokes equations. The Bladwin and Lomax algebraic turbulence model is used to mimic turbulent flow downstream of a point designated as the transition location. The investigation focuses on the leading edge, where, as experimental results indicate, a recirculating bubble is often present. It is found that the transition location has a dominating effect on the development of the flow and the evolution of the recirculation bubble which, in most cases, is the mechanism leading to the onset of separation and dynamic stall. In cases where the appearance of the bubble is prevented by some particular choices of the transition location, a supersonic region emerges, and numerical instability originated from there halts the simulations.
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 or presentation (such as public display or performance) of protected items is prohibited except with permission of the author.en_US
dc.subjectAerospace engineering.en_US
dc.titleNumerical investigation of the unsteady effect on the onset of leading-edge separation in dynamic stall.en_US
dc.typetexten_US
dc.typeDissertation-Reproduction (electronic)en_US
dc.contributor.chairFung, K.-Y.en_US
dc.identifier.oclc702683617en_US
thesis.degree.grantorUniversity of Arizonaen_US
thesis.degree.leveldoctoralen_US
dc.contributor.committeememberSears, William R.en_US
dc.contributor.committeememberHeinrich, Juan C.en_US
dc.identifier.proquest9408486en_US
thesis.degree.disciplineAerospace and Mechanical Engineeringen_US
thesis.degree.disciplineGraduate Collegeen_US
thesis.degree.namePh.D.en_US
refterms.dateFOA2018-08-23T12:56:28Z
html.description.abstractNumerical experiments are conducted to simulate airfoils pitching up at constant rates into the dynamic stall regime using the Beam and Warming algorithm for compressible Navier-Stokes equations. The Bladwin and Lomax algebraic turbulence model is used to mimic turbulent flow downstream of a point designated as the transition location. The investigation focuses on the leading edge, where, as experimental results indicate, a recirculating bubble is often present. It is found that the transition location has a dominating effect on the development of the flow and the evolution of the recirculation bubble which, in most cases, is the mechanism leading to the onset of separation and dynamic stall. In cases where the appearance of the bubble is prevented by some particular choices of the transition location, a supersonic region emerges, and numerical instability originated from there halts the simulations.


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