Abstract
Initialworkispresentedonanin-e ightstallmargininstrumentationsystemthatmaintainsaccuracyindependent of wing leading-edge ice formations. The system uses four surface pressures, measured aft of the ice formation, from which the aircraft’ s normalized lift coefe cient is determined. The pressure port locations are selected such that the calibration algorithm remains nearly constant as the leading-edge ice shape and thickness change. Windtunnel data are presented for three ice formations, varying in both type and thickness. The indicated normalized lift coefe cient, based on the no ice algorithm, is compared to the actual normalized lift coefe cient under icing conditions. From this comparison, the four port locations were found to be located at 22 and 41% of the chord on the upper wing surface and 41 and 68% on the lower wing surface.
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