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dc.contributorRodríguez Pérez, Ivette María
dc.contributorSoria Guerrero, Manel
dc.contributor.authorDuran Perez, David
dc.date.accessioned2017-06-26T13:54:35Z
dc.date.available2017-06-26T13:54:35Z
dc.date.issued2017-06-20
dc.identifier.urihttp://hdl.handle.net/2117/105871
dc.descriptionSynthetic jets have emerged as fluid devices for active control boundary layer separation and turbulence. In the proposed TFM the interaction of a modelled synthetic h¡jet with a laminar boundary layer will be investigated numerically using a incompressible Navier–Stokes solver.The main goals of the present TFM are oriented to:-The numerical simulation of synthetic jets into a laminar boundary layer and, -to perform a systematic parametrisation of the synthetic jet in order to characterise the level of flow control in the boundary layer.
dc.description.abstractThis report presents a study of the interaction of AFC (specifically, synthetic jets) with the laminar boundary layer of a NACA 0012 airfoil. First of all, in order to understand the phenomenology of Navier-Stokes equations, a spectro-consistent Computational Fluid Dynamics (CFD) code has been developed from scratch. By using a spectro-consistent discretization, the fundamental symmetry properties of the underlying differential operators are preserved. This code also helps to understand how the energy is transported from big to small scales. After solving a paradigmatic problem (TGV) using the aforementioned code, a mature CFD code (Alya) is used to simulate the flow around the NACA 0012 airfoil. Alya software also uses a spectro-consistent code but in Finite Element Method (FEM). Once the reference cases are solved for different angles of attack, a boundary condition representing an idealized synthetic jet is implemented. A systematic parametrization of the synthetic jet has been performed in order to assess the level of flow control in the boundary layer. Results demonstrate that, by selecting a correct combination of actuator frequency and momentum coefficient, the lift coefficient increases while the drag coefficient decreases producing a better lift-to-drag ratio. This aerodynamic improvement implies that a better circulation control is achieved, less noise is produced and less fuel consumption is required. It is also worth noting that, for high angles of attack, it is necessary to perform 3D flow simulations in order to capture the entire physics of the problem
dc.language.isoeng
dc.publisherUniversitat Politècnica de Catalunya
dc.subjectÀrees temàtiques de la UPC::Enginyeria mecànica::Mecànica de fluids
dc.subjectÀrees temàtiques de la UPC::Aeronàutica i espai
dc.subject.lcshComputational fluid dynamics
dc.subject.lcshAerodynamics--Computer simulation
dc.subject.lcshAerodynamics--Mathematical models
dc.titleStudy of the boundary layer flow control using synthetic jets by means of spectro-consistent discretizations
dc.typeMaster thesis
dc.subject.lemacDinàmica de fluids computacional
dc.subject.lemacAerodinàmica -- Simulació per ordinador
dc.subject.lemacAerodinàmica -- Mètodes numèrics
dc.identifier.slug205-1121
dc.rights.accessOpen Access
dc.date.updated2017-06-19T07:39:28Z
dc.audience.educationlevelMàster
dc.audience.mediatorEscola Superior d'Enginyeries Industrial, Aeroespacial i Audiovisual de Terrassa
dc.audience.degreeMÀSTER UNIVERSITARI EN ENGINYERIA AERONÀUTICA (Pla 2014)


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