Determinación de los valores de arrastre y sustentación de las superficies alares de un dron de ala fija

Abstract

In order to design fixed-wing drones it is necessary to analyze mathematically, or through simulations, different airfoils and determine which one is best in the pre-established specifications. For this, the aerodynamic performance and polar drag factors are compared for five similar airfoils used in fixed-wing drones. These factors are determined based on the drag and lift coefficients. In this project, the profile that best meets the established requirements is the E479, which stands out for generating excellent lift and low drag in a range of angles of attack between 5 ° and 8 °. Finally, this work compares the results obtained with the XFLR5 software and its mathematical model based on the XFOIL methodology, with computational simulations by the CFD methodology through the ANSYS software, obtaining approximations of the lift and drag coefficients.