The objective of this research effort was to evaluate the impact of incorporating an additional cooling port downstream between the injector and nozzle throat in the NASA Fast Track chamber. A numerical model of the chamber was developed for the analysis. The analysis did not model ablation but instead correlated the initial ablation rate with the initial nozzle wall temperature distribution. The results of this study provide guidance in the development of a potentially lighter, second generation ablative rocket nozzle which maintains desired performance levels.
Numerical Simulation of Film-Cooled Ablative Rocket Nozzles
1996
39 pages
Report
No indication
English
Development of Composite Ablative Liners for Solid Rocket Motor Flex Nozzles
Online Contents | 2013
|Kinetic performance of barrier-cooled rocket nozzles.
AIAA | 1968
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