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Finite element thermal analysis of convectively-cooled aircraft structuresThe design complexity and size of convectively-cooled engine and airframe structures for hypersonic transports necessitate the use of large general purpose computer programs for both thermal and structural analyses. Generally thermal analyses are based on the lumped-parameter finite difference technique, and structural analyses are based on the finite element technique. Differences in these techniques make it difficult to achieve an efficient interface. It appears, therefore, desirable to conduct an integrated analysis based on a common technique. A summary is provided of efforts by NASA concerned with the development of an integrated thermal structural analysis capability using the finite element method. Particular attention is given to the development of conduction/forced-convection finite element methodology and applications which illustrate the capabilities of the developed concepts.
Document ID
19820045030
Acquisition Source
Legacy CDMS
Document Type
Other - Collected Works
Authors
Wieting, A. R.
(NASA Langley Research Center Hampton, VA, United States)
Thornton, E. A.
(Old Dominion University Norfolk, VA, United States)
Date Acquired
August 10, 2013
Publication Date
January 1, 1981
Subject Category
Aircraft Design, Testing And Performance
Accession Number
82A28565
Distribution Limits
Public
Copyright
Other

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