Otimização de um aerofólio utilizando o método Parsec de parametrizção

Abstract

This work describes an optimization process of a NACA 4-digit airfoil, that could be selected to be used in a fixed-wing UAV project. This process consists basically of the parameterization of the airfoil's geometry through Parsec method, and optimization codes using the softwares MATLAB and X-Foil. The latter one is highly rated in the aviation sector and widely used in aircraft industry. With this process, the goal was to minimize the original profile’s lowest drag coefficient in order to obtain a more favorable performance for the flight conditions proposed, with aerodynamic coefficients at angles of attack in cruising flight that provides lower resistance to the aircraft movement, because the purpose is to optimize a long endurance airfoil. The goal was achieved for a small range in the angles of attack interval taken as reference, next to the level flight