Spatial Load Distribution in Composite Flapping Wing Under Small Deformation

Abstract

Present study reports the theoretically supported wind tunnel experimental investigations on the load distribution in a flapping wing under low amplitude flapping. Wind tunnel experiments are performed at 2, 4 and 6 m/s wind speed for hummingbird inspired nanocomposite wing. The spatial deformations fields are obtained from Digital image correlation (DIC). Modified Theodorsen lift theory is implemented to obtain load distribution from the local chord deformations to obtain aerodynamic loads. Three spatial locations at 25, 50 and 75% wing-span are considered for deformation data. The theoretical formulation was used to separate out the inertial and aerodynamic components of loads. Results reveal that the mid-stroke deformation mostly contributes for the aerodynamic lift, while all other deformation instants represent the dominance of inertial loads. © The Author(s), under exclusive license to Springer Nature Singapore Pte Ltd. 2025.