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Modern Airfoil Ice AccretionsThis report presents results from the first icing tests performed in the Modem Airfoils program. Two airfoils have been subjected to icing tests in the NASA Lewis Icing Research Tunnel (IRT). Both airfoils were two dimensional airfoils; one was representative of a commercial transport airfoil while the other was representative of a business jet airfoil. The icing test conditions were selected from the FAR Appendix C envelopes. Effects on aerodynamic performance are presented including the effects of varying amounts of glaze ice as well as the effects of approximately the same amounts of glaze, mixed, and rime ice. Actual ice shapes obtained in these tests are also presented for these cases. In addition, comparisons are shown between ice shapes from the tests and ice shapes predicted by the computer code, LEWICE for similar conditions. Significant results from the tests are that relatively small amounts of ice can have nearly as much effect on airfoil lift coefficient as much greater amounts of ice and that glaze ice usually has a more detrimental effect than either rime or mixed ice. LEWICE predictions of ice shapes, in general, compared reasonably well with ice shapes obtained in the IRT, although differences in details of the ice shapes were observed.
Document ID
19970017671
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Addy, Harold E., Jr. (NASA Lewis Research Center Cleveland, OH United States)
Potapczuk, Mark G. (NASA Lewis Research Center Cleveland, OH United States)
Sheldon, David W. (NASA Lewis Research Center Cleveland, OH United States)
Date Acquired
September 6, 2013
Publication Date
March 1, 1997
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-107423
AIAA Paper 97-0174
E-10667
NAS 1.15:107423
Report Number: NASA-TM-107423
Report Number: AIAA Paper 97-0174
Report Number: E-10667
Report Number: NAS 1.15:107423
Meeting Information
Meeting: Aerospace Sciences
Location: Reno, NV
Country: United States
Start Date: January 6, 1997
End Date: January 10, 1997
Sponsors: American Inst. of Aeronautics and Astronautics
Accession Number
97N19835
Funding Number(s)
PROJECT: RTOP 505-68-1C
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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