In the effort to improve the flight performance of small aircraft in unsteady flight conditions, inspiration is taken from a lift-enhancing structure found on avian wings called the alula. A finite-span, forward-swept trailing edge, and unswept leading edge wing model was outfitted with alula-like vortex generators and tested in a wind tunnel at a mean-chord-based Reynolds number of 100,000. Alula deflection angles of 𝜹 = 10◦, 20◦, and 30◦ relative to the leading edge were tested, including versions with and without gaps. Using a dynamic motion positioning system equipped with a sting balance, aerodynamic load and moment measurements were acquired to understand the alula’s impact on the loads in both steady and dynamic conditions. Oil flow visualization was performed to make observations on the surface topology. The presence of the alula is shown to delay stall and pitch break. It also reduces drag pre-stall, and reduces yaw and roll moments associated with localized stall. Oil flow visualization results corroborate these observations, as a reduction in the inverted ram’s horn vortex, associated with forward swept wing stall, was observed. The alula was also shown to reduce dynamic stall hysteresis during ramp-up/ramp-down pitching motion. Of the alula geometries tested, the 𝜹 = 10◦ showed the best improvements to lift.