TRANSPIRATION AND FILM COOLING FOR SOLID PROPELLANT ROCKET NOZZLES
Abstract
The fundamental aspects of film cooling and transpiration cooling employed as thermal protection systems for solid-propellant rocket nozzles were studied in detail. Liquid evaporative film cooling and two-phase transpiration cooling appear to be the most attractive systems. While the studies have indicated that evaporative liquid film cooling is an immediately applicable thermal protection system, the experimental results show that a two-phase transpiration system is fundamentally stable in operation, and offers advantages from a coolant weight requirement standpoint. A concept for an experimental, transpiration-cooled nozzle was presented in preparation for additional experiments. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 07, 1961
- Accession Number
- AD0273333
Entities
People
- Carson Kuo
- Seymour Hyman