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- W2003274103 abstract "Numerical 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." @default.
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- W2003274103 date "1992-01-06" @default.
- W2003274103 modified "2023-10-14" @default.
- W2003274103 title "Integrated numerical methods for hypersonic aircraft cooling systemsanalysis" @default.
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- W2003274103 doi "https://doi.org/10.2514/6.1992-254" @default.
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