SELF-COOLED ROCKET NOZZLES, VOLUME 2.
Abstract
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1964
- Accession Number
- AD0601574
Entities
People
- F. B. Gessner
- J. D. Seader
- R. J. Ingram
Organizations
- Rocketdyne