Accession Number : AD0473111


Title :   Effect of Rocket Engine Combustion on Chamber Materials. Part 2. Two-Dimensional Computer Program


Descriptive Note : Final rept


Corporate Author : ROCKETDYNE CANOGA PARK CA


Personal Author(s) : Friedman, H A ; Persselin, S F ; McFarland, B L ; Seader, J D


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/473111.pdf


Report Date : Sep 1965


Pagination or Media Count : 160


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.


Descriptors :   *ROCKET ENGINE CASES , ABLATION , STABILITY , CORROSION , EROSION , CHEMICAL REACTIONS , ROCKET NOZZLES , LIQUID PROPELLANT ROCKET ENGINES , TABLES(DATA) , NUMERICAL METHODS AND PROCEDURES , PYROLYSIS , HEAT TRANSFER , THERMAL CONDUCTIVITY


Subject Categories : Rockets
      Computer Programming and Software


Distribution Statement : APPROVED FOR PUBLIC RELEASE