Aerodynamic characterization of a thin, high-performance airfoil for use in ground fluids testing

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Proceedings title5th AIAA Atmospheric and Space Environments Conference
Conference5th AIAA Atmospheric and Space Environments Conference, 24 June 2013 through 27 June 2013, San Diego, CA
SubjectAero-dynamic performance; Aerodynamic characterization; Aerodynamic effect; Anti-icing fluids; Flow disturbances; Laminar separation bubble; National Research Council of Canada; Wind-tunnel testing; Contamination; Data visualization; Ice; Laminar flow; Pelletizing; Reynolds number; Wind tunnels; Aerodynamics
AbstractThe FAA has worked with Transport Canada and others to develop allowance times for aircraft operating in ice-pellet precipitation. Wind-tunnel testing has been carried out to better understand the flowoff characteristics and resulting aerodynamic effects of anti-icing fluids contaminated with ice pellets using a thin, high-performance wing section at the National Research Council of Canada Propulsion and Icing Wind Tunnel. The objective of this paper is to characterize the aerodynamic behavior of this wing section in order to better understand the adverse aerodynamic effects of anti-icing fluids and ice-pellet contamination. Aerodynamic performance data, boundary-layer surveys and flow visualization were conducted at a Reynolds number of approximately 6.0×106 and a Mach number of 0.12. The clean, baseline model exhibited leading-edge stall characteristics including a leading-edge laminar separation bubble and minimal or no separation on the trailing edge of the main element or flap. These results were consistent with expected 2-D aerodynamics and showed no anomalies that could adversely affect the evaluation of anti-icing fluids and ice-pellet contamination on the wing. Tests conducted with roughness and leading-edge flow disturbances helped to explain the aerodynamic impact of the anti-icing fluids and contamination. The stalling characteristics of the wing section with fluid and contamination appear to be driven at least partially by the effects of a secondary wave of fluid that forms near the leading edge as the wing is rotated in the simulated takeoff profile. These results have provided a much more complete understanding of the adverse aerodynamic effects of anti-icing fluids and ice-pellet contamination on this wing section. This is important since these results are used, in part, to develop the ice-pellet allowance times that are applicable to many different airplanes.
Publication date
AffiliationNational Research Council Canada (NRC-CNRC)
Peer reviewedYes
NPARC number21269972
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Record identifierc4b96a58-1332-4bad-816d-63ec3df224ce
Record created2013-12-13
Record modified2016-05-09
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