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.


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    Title :

    Integrated numerical methods for hypersonic aircraft cooling systems analysis


    Additional title:

    Integrierte numerische Methoden für die Untersuchung von Kühlsystemen für Luftfahrzeuge


    Contributors:
    Petley, D.H. (author) / Jones, S.C. (author) / Dziedzic, W.M. (author)

    Published in:

    Publication date :

    1992


    Size :

    11 Seiten, 18 Bilder, 12 Quellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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