Measurements of lift, drag and pitching moment of an NACA 0011 airfoil were, made in icing using two types of pneumatic de-icers, one having spanwise inflatable tubes and the other having chordwise tubes. Ice remaining after inflation of the spanwise-tube deicer increased airfoil section drag 7 to 37 percent for 0° to 4.6° angle of attack over the ranges of airspeed, total air temperature, liquid-water content, and cycle times covered. This drag increase became constant after a few deicing cycles. Drag increases due to ice remaining on the chordwise-tube de-icer were similar to those for the spanwise-tube deicer. Minimum airfoil drag in icing (averaged over a de-icing cycle) was usually ob¬tained with a short (about 1 min) de-icing cycle.
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