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.
Integrated numerical methods for hypersonic aircraft cooling systems analysis
1992-01-01
Conference paper
No indication
English
Integrated numerical methods for hypersonic aircraft cooling systems analysis
Tema Archive | 1992
|Analysis of cooling systems for hypersonic aircraft
AIAA | 1991
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