Numerical simulation and experimental validation of slender wings flutter behaviour

The flutter instability of high aspect ratio wings is numerically investigated by means of finite element aeroelastic analysis. The effect of static equilibrium deflection as well as the additional differential stiffness was introduced in the calculation by a new procedure based on MSC Nastran (TM) commercial code. The difference between the classic linear flutter calculation and the new procedure presented has been demonstrated numerically and also experimentally. The main parameters that influence the aeroelastic phenomenon were also highlighted and used to define the aeroelastic similarity model related to a typical aircraft of the high altitude long endurance aircraft category.