Effect of Rocket Engine Combustion on Chamber Materials. Part 2. Two-Dimensional Computer Program
Abstract
An implicit finite difference procedure was developed for solving a general class of two dimensional transient non-linear ablation and heat conduction problems for rocket engine thrust chamber walls. Firing may be steady or can consist of multiple start or pulsing type modes. Different wall materials may be treated in a given problem including one charring ablative material. Temperature dependent properties may be specified for each material. Chemical reactions within the ablative material are handled in depth. Surface erosion due to chemical reactions or melting at the hot gas boundary is treated and the resulting surface recession is predicted. The numerical procedures were programmed in Fortran IV for automatic computation. Comparison of the results of sample computations with actual engine test firing data is included.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1965
- Accession Number
- AD0473111
Entities
People
- B. L. Mcfarland
- H. A. Friedman
- J. D. Seader
- S. F. Persselin