Análise numérica do escoamento em perfis aerodinâmicos com dispositivos hipersustentadores

Abstract

In the aeronautical sector, a type of geometry widely used in studies in aerodynamics are the high lift devices. These bodies located on the leading and treailing edges of the aircraft’s wings are responsible for increasing lift, for example, during takeoff and landing where the aerodynamic conditions are different, the wings need these devices to obtain the necessary lift coefficient. This work presentes a study of the flow dynamic involving the aerodynamic airfoil NACA0012 with and without high lift devices, where the objective is to have a better understanding of the effects involved and to define among the evaluated geometries, the one with the best performance in maximixing lift and reduce drag. For the numerical studies, the Navier-Stokes equations were solved to obtain the results using the COMSOL Multiphysics software, which is based on the Finite Element Method. All simulations were carried out in the Heat Transfer Laboratory (LabTC) on the Federal University of Itajubá. Initially, the simulations were performed on the NACA0012 airfoil, called the base airfoil, and then a flap at 10° was added to its trailing edge. It was observed that the addition of the flap generates an increase in the values of the lift and drag coefficients for the same angle of attack. A third test was carried out for the base airfoil with the addition of the flap, where the base airfoil was fixed at 7° and the flap angle was varied, showing that as the angle increases the lift coefficient also increases, this occurs due to the increased curvature of the airfoil. Another simulation performed was adding a slat on the leading edge, proving the this device postpones the stall. Finally, a test was carried out adding a slat and a flap to the base airfoil, stating that the combination of these three elements generates a higher value of the lift coeficiente and a better distribution of the pressure coeficiente. Based on the angle of attack variation, it were performed qualitative and quantitative analyzes of the results of the streamline fields, vorticity fields, pressure fields and aerodynamic coefficients for a Reynolds number equal 1000.