Lift and pitching moment wind-tunnel data was obtained for Miniature-Trailing Edge Effectors (MiTEs). Unsteady data was acquired, non-dimensionalized, and compared to numerical predictions. A 0.02c height MiTE located at 0.9c was employed, which provided the same lift enhancement as a 0.17c trailing edge flap deflected 8 degrees. Aerodynamic loads of both types of flaps at a reduced frequency of 0.21 and a Reynolds number of 1.0 ×106 were recorded. The results were interpreted using previously verified computational fluid dynamics. Experimental results captured the unsteady aerodynamics loads due to strong vortex shedding that occur downstream of the deploying MiTEs. This phenomenon was never measured during prior dynamic testing, and validates computational fluid dynamics predictions.