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Integrated numerical methods for hypersonic aircraft cooling systems analysisNumerical methods have been developed for the analysis of hypersonic aircraft cooling systems. A general purpose finite difference thermal analysis code is used to determine areas which must be cooled. Complex cooling networks of series and parallel flow can be analyzed using a finite difference computer program. Both internal fluid flow and heat transfer are analyzed, because increased heat flow causes a decrease in the flow of the coolant. The steady state solution is a successive point iterative method. The transient analysis uses implicit forward-backward differencing. Several examples of the use of the program in studies of hypersonic aircraft and rockets are provided.
Document ID
19920043088
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Petley, Dennis H.
(NASA Langley Research Center Hampton, VA, United States)
Jones, Stuart C.
(NASA Langley Research Center Hampton, VA, United States)
Dziedzic, William M.
(Lockheed Engineering and Sciences Co. Hampton, VA, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1992
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 92-0254
Accession Number
92A25712
Distribution Limits
Public
Copyright
Other

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