| Abstract | Icing wind tunnel tests were conducted at the National Research Council Canada's 3 m x 6 m Propulsion and Icing Wind Tunnel (PIWT) located in Ottawa, Ontario, Canada early in 2011 and 2012. These tests were a continuation of the work performed in 2010 on a generic supercritical airfoil representative of a regional-jet type aircraft wing section. Tests nominally consisted of coating the wing with de/anti-icing fluid, applying various levels of precipitation (e.g., snow, ice pellets, freezing rain, or combinations thereof), and simulating a take-off condition in the wind tunnel by accelerating the wind speed and pitching the wing through a desired pitch-profile. The wing performance was evaluated primarily by the measured lift-loss relative to the lift generated by a clean wing. The second phase of testing consisted of test cases similar to the 2010 tests in order to expand the scope of the data sets at various temperatures, while also investigating the effects of the rotation speed and ramp time on lift-loss and the effects of fluids and precipitation on stall. The experimental results were used as guidance for regulators in determining holdover and allowance times for aircraft operating in winter precipitation. © 2012 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. |
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