Flutter in Aircraft Wings Under Subsonic Flow Conditions
The influence of flutter in aircraft wings under subsonic flow conditions was studied. Flutter is a type of self-excited system state that can lead to instability. The parameters that have been considered are: angle of attack, no aileron, no flutter in the aircraft tail and control surface. To simplify the problem further, the focus of this study was only on the fundamental wing bending and torsion. For the fundamental wing bending the equations considered to get the flutter stability determinants were: kinetic energy and potential energy. These formulas were used to get the graphic of the curve that shows the beginning of the critical flutter speed. The major objective was to prevent flutter problems in aircraft wings using the solution of differential equations to get the critical flutter speed curve. To analyze and prevent this kind of phenomenon, Matlab software was used as a simulation tool. The unsteady aerodynamic theory used was that of the two dimensional flutter problems from Theodore and Garrick.
School:
Universidad Del Turabo
Department:
Engineering / Aerospace and Structures
Research Advisor:
Harry Hilton
Department of Research Advisor:
Aerospace Engineering
Year of Publication:
2008