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User Manual for the NASA Glenn Ice Accretion Code LEWICE: Version 2.0

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TLDR
In this article, the authors present a description of the code inputs and outputs from version 2.2 of this code, which is called LEWICE, and compare the results against the database of electrothermal results generated in the NASA Glenn Icing Research Tunnel (IRT).
Abstract
A research project is underway at NASA Glenn to produce a computer code which can accurately predict ice growth under a wide range of meteorological conditions for any aircraft surface. This report will present a description of the code inputs and outputs from version 2.2.2 of this code, which is called LEWICE. This version differs from release 2.0 due to the addition of advanced thermal analysis capabilities for de-icing and anti-icing applications using electrothermal heaters or bleed air applications. An extensive effort was also undertaken to compare the results against the database of electrothermal results which have been generated in the NASA Glenn Icing Research Tunnel (IRT) as was performed for the validation effort for version 2.0. This report will primarily describe the features of the software related to the use of the program. Appendix A of this report has been included to list some of the inner workings of the software or the physical models used. This information is also available in the form of several unpublished documents internal to NASA. This report is intended as a replacement for all previous user manuals of LEWICE. In addition to describing the changes and improvements made for this version, information from previous manuals may be duplicated so that the user will not need to consult previous manuals to use this code.

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An experimental investigation on the unsteady heat transfer process over an ice accreting airfoil surface

TL;DR: In this article, an experimental investigation was performed in an Icing Research Tunnel available at Iowa State University (i.e., ISU-IRT) to quantify the unsteady heat transfer and dynamic ice accretion process over an airfoil/wing surface under different icing conditions.
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References
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Book ChapterDOI

Boundary Layer Theory

TL;DR: The boundary layer equations for plane, incompressible, and steady flow are described in this paper, where the boundary layer equation for plane incompressibility is defined in terms of boundary layers.

Theory of Wing Sections

TL;DR: Chang et al. as discussed by the authors proposed a new geometric analysis procedure for wing sections based on the normal mode analysis for continuous functions, which can be used to calculate the section length.
BookDOI

Viscous fluid flow

TL;DR: In this article, the authors present the principles of control volume early for use throughout the book and emphasize the constitutive equation that relates deformation to stress, which can be easily generalized to non-Newtonian fluids mechanics.
Journal ArticleDOI

The automatic integration of ordinary differential equations

TL;DR: An integration technique for the automatic solution of an initial value problem for a set of ordinary differential equations and a criterion for the selection of the order of approximation are proposed.