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Lewis icing research tunnel test of the aerodynamic effects of aircraft ground deicing/anti-icing fluidsA wind tunnel investigation of the effect of aircraft ground deicing/anti-icing fluids on the aerodynamic characteristics of a Boeing 737-200ADV airplane was conducted. The test was carried out in the NASA Lewis Icing Research Tunnel. Fluids tested include a Newtonian deicing fluid, three non-Newtonian anti-icing fluids commercially available during or before 1988, and eight new experimental non-Newtonian fluids developed by four fluid manufacturers. The results show that fluids remain on the wind after liftoff and cause a measurable lift loss and drag increase. These effects are dependent on the high-lift configuration and on the temperature. For a configuration with a high-lift leading-edge device, the fluid effect is largest at the maximum lift condition. The fluid aerodynamic effects are related to the magnitude of the fluid surface roughness, particularly in the first 30 percent chord. The experimental fluids show a significant reduction in aerodynamic effects.
Document ID
19920021152
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Runyan, L. James (Boeing Commercial Airplane Co. Seattle, WA., United States)
Zierten, Thomas A. (Boeing Commercial Airplane Co. Seattle, WA., United States)
Hill, Eugene G. (Boeing Commercial Airplane Co. Seattle, WA., United States)
Addy, Harold E., Jr. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 6, 2013
Publication Date
August 1, 1992
Subject Category
Air Transportation And Safety
Report/Patent Number
E-5808
NASA-TP-3238
NAS 1.15:3238
Accession Number
92N30395
Funding Number(s)
PROJECT: RTOP 505-68-11
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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