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Numerical simulation of two-dimensional heat transfer in composite bodies with application to de-icing of aircraft componentsTransient, numerical simulations of the de-icing of composite aircraft components by electrothermal heating were performed for a two dimensional rectangular geometry. The implicit Crank-Nicolson formulation was used to insure stability of the finite-difference heat conduction equations and the phase change in the ice layer was simulated using the Enthalpy method. The Gauss-Seidel point iterative method was used to solve the system of difference equations. Numerical solutions illustrating de-icer performance for various composite aircraft structures and environmental conditions are presented. Comparisons are made with previous studies. The simulation can also be used to solve a variety of other heat conduction problems involving composite bodies.
Document ID
19840005422
Acquisition Source
Legacy CDMS
Document Type
Thesis/Dissertation
Authors
Chao, D. F. K. (Toledo Univ. OH, United States)
Date Acquired
September 4, 2013
Publication Date
November 1, 1983
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
NASA-CR-168283
NAS 1.26:168283
Accession Number
84N13490
Funding Number(s)
CONTRACT_GRANT: NAG3-72
PROJECT: RTOP 505-45-02
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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