Computational aeroelastic analysis of AGARD 445.6 wing using open-source software

The transonic regime between 08-1.2 Mach, where the flight speed is around the speed of sound, experienced during the transition of the aircraft from subsonic to supersonic regime is called transonic regime. Although the aircraft itself is traveling at less than the speed of sound in this regime, the airspeed circulating around it may exceed the speed of sound at some points. In regions where the local air velocity is close to or higher than the speed of sound, compressibility effects occur and a separation in the boundary layer occurs behind the shock due to the interaction of the shock wave and the boundary layer. Classical flutter methods are not sufficient to determine the aeroelastic behavior of aircraft flying in the transonic regime where such complex flow events occur. In recent years, studies to determine flutter instabilities of transonic aircraft have become widespread, but the first of these studies is the AGARD 445.6 wing, which is an experimental study and has become a standard for the verification of computational aeroelastic codes today. In this study, it is aimed to obtain flutter instabilities of the AGARD 445.6 wing using fully open source software and to compare the results with the experimental results. Each of the stages of geometry and mesh creation (GMSH), solution (SU2, Calculix) and displaying the results (Paraview) were carried out with open source software. CFD methods for fluid and the coupling of discrete solvers using Computational Structural Dynamics (CSD) methods for structure are made with PreCICE software, which is an open source library. Mutual comparisons were made by creating highly accurate models for both fluid and structure solution.