In this study, experimental airfoil data was taken in the Laminar Wind Tunnel of the Technical University of Berlin. A NACA0021 airfoil was tested with various sizes and positions of static microtabs while the foil underwent pitching oscillations. The resulting data was analysed using the novel Hilbert Transform method to yield the instantaneous aerodynamic damping. From this analysis it was possible to determine that in light and deep stall, microtabs increase the cycle averaged aerodynamic damping but in the case of light stall, the microtabs amplify the sub-cycle negative damping regions as well. This yields the conclusion that sub-cycle actuation of the microtab in light stall could further optimise the aerodynamic damping. The aforementioned effects get stronger with increasing tab size and as the microtabs are positioned further forward.