Desenvolvimento e implementação de um procedimento numérico para cálculo de conjuntos asa-empenagens de geometria complexa em regime de vôo subsônico, assimétrico e não linear

Abstract

This work presents the development and computer implementation of anumeric procedure for estimation of aerodynamic characteristics of wing-tail groups in subsonic environments. The bi-dimensional procedure is based on the Panel Method using empirical models of boundary layers. The tri-dimensional procedure is based on the Vortex-Lattice Method; however, its formulation permits the prediction of the aerodynamic characteristics in a non-linear way, below and above the stall, through the utilization of the bi-dimensional airfoil characteristics that composes the wing and tail and in non-symmetrical flight conditions. Its also included a free wake model and induced drag measurement through the Momentum variation. Through the comparison with similar others softwares and experimental results is demonstrated its advantages, trustworthiness and flexibility. This procedure was showed as highly recommendable for the solution of the typical problems in project of subsonic aircrafts, supplying the necessities since the initial phases until more advanced phases of project, being able also to be used for optimization and flight simulation, due to the necessary lowcomputational cost.