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
Integrierte numerische Methoden für die Untersuchung von Kühlsystemen für Luftfahrzeuge
AIAA-Papers ; 1-11
1992
11 Seiten, 18 Bilder, 12 Quellen
Conference paper
English