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dc.contributor.authorHoffman J.
dc.contributor.authorJansson J.
dc.contributor.authorJansson N.
dc.contributor.authorde Abreu R.V.
dc.date.accessioned2016-06-13T13:10:31Z
dc.date.available2016-06-13T13:10:31Z
dc.date.issued2014-12-31
dc.identifier.isbn978-1-624-10256-1
dc.identifier.urihttp://hdl.handle.net/20.500.11824/60
dc.description.abstractWe present a time-resolved, adaptive finite element method for aerodynamics, together with the results from the HiLiftPW-2 workshop, where this method is used to compute the ow past a DLR-F11 aircraft model at realistic Reynolds number. The mesh is automatically constructed by the method as part of the computation, and no explicit turbulence model is used. The effect of unresolved turbulent boundary layers is modeled by a simple parametrization of the wall shear stress in terms of the skin friction. In the extreme case of very high Reynolds numbers we approximate the small skin friction by zero skin friction, corresponding to a free slip boundary condition, which results in a computational model without any model parameter that needs tuning. Thus, the simulation methodology bypasses the main challenges posed by high Reynolds number CFD: the design of an optimal computational mesh, turbulence (or subgrid) modeling, and the cost of boundary layer res- olution. The results from HiLiftPW-2 presented in this report show good agreement with experimental data for a range of different angles of attack, while using orders of magnitude fewer degrees of freedom than what is needed in state of the art methods such as RANS.
dc.formatapplication/pdf
dc.languageeng
dc.publisher52nd AIAA Aerospace Sciences Meeting - AIAA Science and Technology Forum and Exposition, SciTech 2014
dc.rightsinfo:eu-repo/semantics/openAccess
dc.rights.urihttp://creativecommons.org/licenses/by-nc-sa/3.0/es/
dc.subjectAerospace engineering
dc.subjectAircraft models
dc.subjectFinite element method
dc.subjectReynolds number
dc.subjectSkin friction
dc.subjectTurbulence models
dc.subjectAdaptive finite element methods
dc.subjectComputational model
dc.subjectFree-slip boundary conditions
dc.subjectHigh Reynolds number
dc.subjectOrders of magnitude
dc.subjectSimulation methodology
dc.subjectState-of-the-art methods
dc.subjectTurbulent boundary layers
dc.subjectAerodynamics
dc.titleTime-resolved adaptive FEM simulation of the DLR-F11 aircraft model at high Reynolds number
dc.typeinfo:eu-repo/semantics/conferenceObject
dc.typeinfo:eu-repo/semantics/acceptedVersion
dc.relation.publisherversionhttp://arc.aiaa.org/doi/abs/10.2514/6.2014-0917


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