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.