Is this project an undergraduate, graduate, or faculty project?
Undergraduate
individual
What campus are you from?
Daytona Beach
Authors' Class Standing
Daniel de la Peña Jiménez, senior
Lead Presenter's Name
Daniel de la Peña Jiménez
Faculty Mentor Name
A. Vega Coso, Universidad Europea de Madrid
Abstract
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. These couplings occur when the aerodynamic forces associated with motion in two modes of vibration cause the modes to couple in an unfavorable manner. The characteristic equation will be analyzed and derived in order to study stability and its relationship with the damping ratios of the aircraft wing. Analytical analysis of different mode shapes will be carried out by means of applying Newton’s equation of motion and time-dependent boundary conditions. Underdamped, critically damped, over-damped and flutter diagrams will be obtained for different damping ratios. Furthermore, these diagrams will be compared with analytical derivations. Those results indicate stability dependence on damping ratio as it is basically a free vibration problem. Comparison between different models shows accurate results. Further research is focused on considering and proving detailed results on experimental data on lab.
Did this research project receive funding support from the Office of Undergraduate Research.
No
Flutter Stability Analysis of an Aircraft Wing as a Function of Damping Ratio
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. These couplings occur when the aerodynamic forces associated with motion in two modes of vibration cause the modes to couple in an unfavorable manner. The characteristic equation will be analyzed and derived in order to study stability and its relationship with the damping ratios of the aircraft wing. Analytical analysis of different mode shapes will be carried out by means of applying Newton’s equation of motion and time-dependent boundary conditions. Underdamped, critically damped, over-damped and flutter diagrams will be obtained for different damping ratios. Furthermore, these diagrams will be compared with analytical derivations. Those results indicate stability dependence on damping ratio as it is basically a free vibration problem. Comparison between different models shows accurate results. Further research is focused on considering and proving detailed results on experimental data on lab.