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Aerodynamic Effects Of Deicing And Anti-Icing FluidsReport presents results of wind-tunnel tests of aerodynamic effects of deicing and anti-icing fluids on airplane wings. Tests conducted on three-dimensional half-model airplane and two-dimensional airfoil model at temperatures ranging from -29 to +10 degrees C. Fluids used included three commercial fluids available for use during 1987-1988 winter season, one discontinued commercial fluid, and eight newer fluids experimental at time of test.
Document ID
19940000091
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Tech Brief
Authors
Addy, Harold E., Jr. (NASA Lewis Research Center, Cleveland, OH.)
Runyan, L. James (Boeing Commercial Airplanes)
Zierten, Thomas A. (Boeing Commercial Airplanes)
Hill, Eugene G. (Boeing Commercial Airplanes)
Date Acquired
August 16, 2013
Publication Date
February 1, 1994
Publication Information
Publication: NASA Tech Briefs
Volume: 18
Issue: 2
ISSN: 0145-319X
Subject Category
Physical Sciences
Report/Patent Number
LEW-15746
Accession Number
94B10091
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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