Airfoil-flap performance with de/anti-icing fluids and freezing precipitation

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TypeTechnical Report
Series titleTransport Canada Report; no. TP 13426E
Physical descriptionxii, 14 p.
Subjectaircraft ground icing; de-icing fluids; anti-icing fluids; freezing precipitation; snow
AbstractWind tunnel tests were performed to measure the aerodynamic performance effects of de- and anti-icing fluids that had been contaminated by varying quantities of freezing precipitation. The experiments were carried out in the National Research Council Canada's 3 m x 6 m open circuit wind tunnel over three winter seasons. The airfoil tested was a full-scale NASA LS(1)-0417 section with a Fowler flap deployed at 15 degrees. A spray bar located in the wind tunnel settling chamber produced artificial snow. Takeoff was simulated by accelerating the test section wind speed and aerodynamic data were obtained while pitching the airfoil to the stall. The experiments consistently showed that the lift loss associated with the snowfall contamination of de- and anti-icing fluids on the airfoil increases rapidly once the fluids can no longer absorb the falling snow crystals. This accelerated lift loss coincides with the visual failure of the fluid, that is, with the formation of a layer of snow on the fluid. The contamination periods required to reach the visual and aerodynamic failure of the fluid were generally consistent with the Society of Automotive Engineers (SAE) standard holdover times that corresponded to the test conditions.
Publication date
AffiliationNRC Institute for Aerospace Research; National Research Council Canada
Access conditionavailable
Peer reviewedNo
NRC numberAL-1999-0115
NPARC number8932573
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Record identifier896bab91-f27b-4d35-9910-eb3f126f1eb9
Record created2009-04-23
Record modified2017-04-26
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