Abstract
The design of novel airfoils for airplanes invariably demands new knowledge of aerodynamics. PARametric SECtion (PARSEC) airfoil representation is one of the most promising methods for automated airfoil/wing design. However, because the airfoil parameterization was originally carried out for transonic flows, it may be difficult to extend its application to unknown flow conditions, including the low Reynolds number (Re) flow case. In this study, the representation of the PARSEC method is modified, especially around the leading-edge and applied to airfoil design using a multi-objective genetic algorithm, leading to an optimal design for potential development and use in a Martian airplane. Correspondingly, an airfoil that can obtain a sufficient lift and glide ratio under lower thrust conditions is considered. The objective functions aim towards maximizing the maximum lift-to-drag ratio generated and towards minimizing the drag at the maximum lift-to-drag ratio. In this way, information on the low Re airfoil could be extracted efficiently. The optimization results indicate that an airfoil with a sharper thickness at the leading-edge and a higher camber at the trailing- edge is more suitable for a Martian airplane.
