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SELF-COOLED ROCKET NOZZLES, VOLUME 2.
ROCKETDYNE CANOGA PARK CALIF
A detailed analytical heat transfer model was developed for a self-cooled composite nozzle throat inset material. The analysis was programmed for the IBM 7094 digital computer, and case studies were run for a number of coolants in a tungsten matrix. A fundamental understanding of the selfcooling phenomenon was gained, and the important coolant and matrix variables affecting cooling performance were determined. The capability of self-cooling to improve rocket nozzle performance was demonstrated. The most effective self-cooling effect was described as interface cooling, which was strongly influenced by the porous micro-structure of the matrix and the coolant boiling point. Author
Summary technical rept., volume 2, 1 Jul 62-30 Jun 63,
AF33 657 9166