• Aeroelasticity
• Flutter boundary
• Numerical Analysis

Fluid structure interaction is a study concerning the mutual interaction between the fluid dynamic force on the deformation of a structure and the subsequent deformation of the structure, which in turn modify the boundary condition of the fluid dynamic flow field. The mutual interaction nature of such a phenomena created a coupling effect between the fluid mechanic and solid mechanic problems. The problem of fluid structure interaction occurs in many engineering fields, such as the dynamic behavior of suspension bridge, tall buildings, the turbine and compressor blades in turbo machineries, and of course, the wings of aircrafts.
The mutual interaction nature of such problems posed significant difficulties in analytical modeling, subsequently only for sufficiently simplified problems there exist analytical closed form solutions. For most of the problems encountered in practice, the practical approaches to analyze these problem are either experimental or numerical, or both.
The work of this thesis concern with fluid structure interaction of aircraft wing, also known as aero elasticity problem. More specifically, it deal with the structural dynamic behavior of the wing submerge in a moving stream of fluid. It was known from past aviation experience and test flight that a lifting surface such as a wing, will experience unstable dynamic response in certain flight conditions. This unstable dynamic response of the wing under these flight conditions are commonly referred to as the flutter. When flutter occurs, the deformation of the wing will undergo an oscillatory motion with increasing amplitude, often results in structural damage or even failure of the wing.
The aim of this thesis is to numerically study the flow condition under which flutter occur, using the fluidstructure-interaction capability of the commercial software Ansys Workbench. Subsequently explore possibility of using a curved wing configuration to delay the onset of flutter, especially in the transonic flight regime (the transonic dip). The experimental test case from the AGARD Report No.765 is chosen as a benchmark for comparison and validation of this study, with air as the fluid.