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Validation of NASA Thermal Ice Protection Computer Codes: The Validation of Antice - Part 3An experimental program was generated by the Icing Technology Branch at NASA Glenn Research Center to validate two ice protection simulation codes: (1) LEWICE/Thermal for transient electrothermal de-icing and anti-icing simulations, and (2) ANTICE for steady state hot gas and electrothermal anti-icing simulations. An electrothermal ice protection system was designed and constructed integral to a 36 inch chord NACA0012 airfoil. The model was fully instrumented with thermo-couples, RTD'S, and heat flux gages. Tests were conducted at several icing environmental conditions during a two week period at the NASA Glenn Icing Research Tunnel. Experimental results of running-wet and evaporative cases were compared to the ANTICE computer code predictions and are presented in this paper.
Document ID
20010068034
Acquisition Source
Glenn Research Center
Document Type
Preprint (Draft being sent to journal)
Authors
Al-Khalil, Kamel M. (Cox and Co., Inc. New York, NY United States)
Horvath, Charles (Cox and Co., Inc. New York, NY United States)
Miller, Dean R. (NASA Glenn Research Center Cleveland, OH United States)
Wright, William B. (NYMA, Inc. Brook Park, OH United States)
Date Acquired
September 7, 2013
Publication Date
May 1, 2001
Subject Category
Air Transportation And Safety
Report/Patent Number
AIAA Paper 97-0051
E-12786/PT3
NAS 1.15:210907/PT3
NASA/TM-2001-210907/PT3
Report Number: AIAA Paper 97-0051
Report Number: E-12786/PT3
Report Number: NAS 1.15:210907/PT3
Report Number: NASA/TM-2001-210907/PT3
Meeting Information
Meeting: 35th Aerospace Sciences Meeting and Exhibit
Location: Reno, NV
Country: United States
Start Date: January 6, 1997
End Date: January 7, 1997
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
PROJECT: RTOP 711-21-23
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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