FLUTTER STABILITY ANALYSIS OF AN AIRCRAFT WING AS A FUNCTION OF THE AEROELASTIC DAMPING RATIO

Descripción

This report provides insight into flutter stability analysis as a function of damping ratio. Flutter, an unstable self-excited vibration in which the structure extracts energy from the air stream and often results in catastrophic structural failure, is analyzed as dynamic instability, which may eventually result in stall or buffeting conditions or classical bending and torsion coupling actions. The characteristic equation of motion is analyzed in order to study stability and its relationship with the damping ratios on an aircraft wing. Analytical results of different mode shapes and time-dependent boundary conditions are provided in this independent research study, under the guidance of PhD. A. Vega Coso. Those results indicate stability dependence on damping ratio as it is basically a free vibration problem. Further research is focused on considering and proving detailed results on experimental data and evaluating aeroelasticity as an essential topic on aircraft design.