A 0.25-inch quarter-round simulated large-droplet ice accretion was tested on a NACA 23012 airfoil with simple flap in the University of Illinois subsonic wind tunnel. The increased drag, in addition to changes in the pitching moment and hinge moment were measured due to the ice simulation. These resulted from a seperation bubble that formed aft of the simulated ice, severly altering the surface pressure distribution. Movement and growth of the ice-induced seperation bubble were observed from florescent-oil flow visualization. The steady-state hing moment became non-linear when flow seperation occurred over the flap and was most affected when the simulated ice accretion was located furthest aft on the upper surface. A sudden change in the flap hing-moment coefficient occurred in the non-linear region of the lift curve, before maximum lift was reached. The fluctuation of the time-dependent hinge moment was measured and characterized by a RMS parameter that exhibited a maximum value at or near maximum lift. The current research relates this unsteady parameter to the steady-state aerodynamic coefficients in addition to the flow characteristics associated with the seperation bubble. As opposed to the steady-state hinge moment, the break in the RMS hinge moment was observed during the linear phase of the lift curve. Thus, the break in the unsteady parameter always occurred before that of the steady-state hinge moment. The RMS hinge-moment coefficient occurred several degrees before stall, providing warning of an impending stall condition due to icing.