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Development of an improved model for runback water on aircraft surfacesA computer simulation for 'running wet' and evaporative aircraft anti-icing systems is developed. The model is based on the analysis of the liquid water film which forms in the regions of direct impingement and, then, breaks up near the impingement limits into rivulets. The wetness factor distribution resulting from the film breakup and the rivulet configuration on the surface are predicted using a stability analysis theory and the laws of mass energy conservation. The solid structure is modeled as a multiple layer wall. The anti-icing system modeled is of the thermal type utilizing hot air and/or electrical heating elements embedded within the wall layers. Experimental observations revealing some of the basic physics of the water flow on the surface are presented. Detailed qualitative documentation of the tests are given. Several numerical examples are considered, and the effect of some of the involved parameters on the system performance are investigated.
Document ID
19920039536
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Al-Khalil, Kamel M.
(National Research Council Washington, DC, United States)
Keith, Theo G., Jr.
(National Academy of Sciences - National Research Council Washington, DC, United States)
De Witt, Kenneth J.
(Toledo, University OH, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1992
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 92-0042
Accession Number
92A22160
Distribution Limits
Public
Copyright
Other

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