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This paper presents results from an extensive experimental study that was conducted to investigate the effect of critical ice accretions on the aerodynamic characteristics of a 24-inch and a 12-inch chord NACA 0011 airfoil section. Aerodynamic performance coefficients as a function of simulated ice horn height and horn angle were measured for chord Reynolds numbers of 1.36~10~ and 1.83 ~10~. Ice shapes were simulated with thin flat plates (spoiler-ice) extending along the span of the wing. A 12-inch chord NACA 0011 airfoil was used for the purpose of investigating ice shape scaling effects on aerodynamic performance. Spoiler-ice shapes with heights of I.5in and 3.0-in were tested with the 24-inch chord airfoil. For the 1Zinch chord airfoil, the corresponding spoiler-ice heights were 0.75in and 1.5in and were obtained from geometric scaling. Lift, drag, pitching moment, and pressure coefficients were obtained with both airfoils for angles of attack ranging from -8 to +17 degrees. The experimental results showed substantial penalties in airfoil aerodynamic performance due to the simulated ice shapes.

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