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Water Droplet Impingement on Simulated Glaze, Mixed, and Rime Ice AccretionsWater droplet impingement data were obtained at the NASA Glenn Icing Research Tunnel (IRT) for a 36-in. chord NACA 23012 airfoil with and without simulated ice using a dye-tracer method. The simulated ice shapes were defined with the NASA Glenn LEWICE 2.2 ice accretion program and including one rime, four mixed and five glaze ice shapes. The impingement experiments were performed with spray clouds having median volumetric diameters of 20, 52, 111, 154, and 236 micron. Comparisons to the experimental data were generated which showed good agreement for the rime and mixed shapes at lower drop sizes. For larger drops sizes LEWICE 2.2 over predicted the collection efficiencies due to droplet splashing effects which were not modeled in the program. Also for the more complex glaze ice shapes interpolation errors resulted in the over prediction of collection efficiencies in cove or shadow regions of ice shapes.
Document ID
Document Type
Technical Memorandum (TM)
Papadakis, Michael
(Wichita State Univ. Wichita, KS, United States)
Rachman, Arief
(Wichita State Univ. Wichita, KS, United States)
Wong, See-Cheuk
(Wichita State Univ. Wichita, KS, United States)
Yeong, Hsiung-Wei
(Wichita State Univ. Wichita, KS, United States)
Hung, Kuohsing E.
(Boeing Co. Wichita, KS, United States)
Vu, Giao T.
(Boeing Co. Wichita, KS, United States)
Bidwell, Colin S.
(NASA Glenn Research Center Cleveland, OH, United States)
Date Acquired
August 24, 2013
Publication Date
October 1, 2007
Subject Category
Air Transportation And Safety
Report/Patent Number
Funding Number(s)
WBS: WBS 22-077-41-08
Distribution Limits
Public Use Permitted.

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