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

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.