Numerical Analysis of MAV's Flapping Wings in Unsteady Conditions

Today, Flapping Micro Aerial Vehicles are used in many different applications. Reynolds Number for this kind of aerial vehicle is about 104 ~ 105 which shows dominancy of inertial effects in comparison of viscous effects in flow field except adjacent of the solid boundaries. Due to periodic flapping stroke, fluid flow is unsteady. In addition, these creatures have some complexities in kinematic modeling. According to these specifications, in present study, a computer code based on the unsteady Panel Method has been developed for flow analysis. The prepared algorithm and the computer code are capable of modeling MAV's flapping wings in different unsteady conditions. The numerical simulation of flapping wings for different conditions of flapping frequencies and wing shapes has been done. The results of aerodynamic design coefficients have been drew. At the end we conclude about the optimum wing shape and flapping frequency are chosen as a result of this study.