DESIGNER'S GUIDE AND COMPUTER PROGRAM FOR ABLATIVE MATERIALS IN LIQUID ROCKET THRUST CHAMBERS
Final rept. 1 Apr 1966-30 Apr 1967
ROCKETDYNE CANOGA PARK CA
Pagination or Media Count:
The two-dimensional ablative heat transfer computer program generated under contract AF04611-9714 was refined and extended to handle anisotropic materials, more than one charring material and reradiation at the heated surface. Results of the two-dimensional program were compared to experimental data to determine effective values of material properties used in the analysis to simulate gas generation and cracking reactions. The resulting effective properties for two ablative materials were used in a parametric study generating basic information for the design of ablative systems in liquid rocket thrust chambers. Graphs and charts showing the variation of thermal penetration, char depth and surface erosion are included.
- Liquid Propellant Rocket Engines