Abstract

In the present research, the effect of incorporating protuberances in the leading edge to the aerofoil NACA-0012 was studied. For the simulations, two profiles were designed: parametric profile (NACA 0012) and modified profile (0012-MOD), with help of CAD Program Inventor Professional 2016. The 0012-MOD profile incorporates modifications in the leading edge, whose inspiration comes from malformations present on the flippers of the humpback whale (Megaptera novaeangliae). The computational simulations were performed in Ansys Fluent, using the turbulent viscosity model k-ε realizable, with SIMPLE calculation algorithm. The study fluid is air in the incompressible range with Ma: 0.11. To obtain the lift and drag curves for both profiles, they were simulated for angles of attack α: between 0° and 40°, this way it will be possible to compare the profiles and determine their aerodynamic behaviour.

In the present research, the effect of incorporating protuberances in the leading edge to the aerofoil NACA-0012 was studied. For the simulations, two profiles were designed: parametric profile (NACA 0012) and modified profile (0012-MOD), with help of CAD Program Inventor Professional 2016. The 0012-MOD profile incorporates modifications in the leading edge, whose inspiration comes from malformations present on the flippers of the humpback whale (Megaptera novaeangliae). The computational simulations were performed in Ansys Fluent, using the turbulent viscosity model k-ε realizable, with SIMPLE calculation algorithm. The study fluid is air in the incompressible range with Ma: 0.11. To obtain the lift and drag curves for both profiles, they were simulated for angles of attack α: between 0° and 40°, this way it will be possible to compare the profiles and determine their aerodynamic behaviour.

Abstract

Uncertainties are a daily issue to deal with in aerospace engineering and applications. Robust optimization methods commonly use a random generation of the inputs and take advantage of multi-point criteria to look for robust solutions accounting with uncertainty definition. From the computational point of view, the application to coupled problems, like computational fluid dynamics (CFD) or fluid–structure interaction (FSI), can be extremely expensive. This study presents a coupling between stochastic analysis techniques and evolutionary optimization algorithms for the definition of a stochastic robust optimization procedure. At first, a stochastic procedure is proposed to be applied into optimization problems. The proposed method has been applied to both CFD and FSI problems for the reduction of drag and flutter, respectively.

Abstract

Environmental pollution is the major concern for all. Renewable energy sources in particular wind and solar play a major role in mitigating pollution. Further to increase energy production by wind power, wind turbines are to be more efficient and should able to operate in low wind regimes. In this research work, the aerodynamic performances are evaluated for the bionic modified bumped blade of an S1223 airfoil. The numerical analysis is carried out with Ansys Fluent tool using turbulent-dissipation model. The aerodynamic performance characteristics such as lift coefficient, drag coefficient are computed and compared with the normal blade. The bionic bumped model produced 11 percent increase in lift coefficient, 20 per cent increase in drag coefficient for the maximum lift producing AoA. The numerically evaluated model can be verified bytesting on real time wind on the field.

Abstract

La presente Tesis de Master tiene como objetivo la modificación del programa CALTEP2000 estacionario, el cual estudia la transmisión de calor mediante el Método de Elementos Finitos (MEF).

Esta modificación pretende adaptar dicho programa al estudio aerodinámico en problemas de fluidos con la aproximación de Flujo Potencial. De esta forma, la adaptación permite soslayar un problema numérico que surge, en fenómenos de flujo alrededor de objetos aerodinámicos que presentan un borde de fuga, si no se toman las precauciones adecuadas.

Una vez obtenida esta adaptación, se procede a validarla con un perfil de ala sencillo y el programa educativo ED-Poiss y, posteriormente, con un cilindro circular y con perfiles NACA-63012A y NACAM-12. Debido a la complejidad de estos últimos, se utiliza para validarlos el programa comercial DesignFOIL, especializado en el estudio de perfiles de ala.