Parametric Study on Wing Flapping Path of a Micro Air Vehicle using Computational Techniques

apping of a two-dimensional wing section of a Micro Air Vehicle (MAV) are presented. First, a computational mesh is created over the wing section of the MAV model. A nite volume based computational ow solver is used to test dierent apping trajectories of the wing section. Finally, a parametric study of the results obtained from the tests is performed. This is a part of the preliminary work required to generate new aerodynamic expressions for a nonlinear dynamic model being developed to study the ight dynamics of the apping MAV. The goal is to understand how dierent parameters aect the aerodynamic force generation by apping motion of a two-dimensional wing in forward ight conditions.