A 2-D Axisymmetric Charring and Ablation Heat Transfer Computer Code
MORTON THIOKOL INC BRIGHAM CITY UT WASATCH OPERATIONS
Pagination or Media Count:
Until recently, the capability to accomplish a two-dimensional axisymmetric nozzle thermal analysis which considers in-depth charring has not been available for rocket nozzle analysis using a standard 2-D axisymmetric conduction code with surface ablation. To alleviate this problem a two-dimensional axisymmetric heat transfer and ablation computer code has been developed which accounts for in-depth decomposition. The code was developed by extensively modifying the Acurex ASTHMA II code to account for in-depth charring, grid generation and material element conductivity based upon the local element coordinate system. The code was also changed to handle as many as 2,000 elements. Code development was based on modeling the material response to a thermal environment in the same way as the one-dimensional Acurex CMA program. Example problems are shown to compare the charring version of ASTHMA ASCHAR to typical CMA models showing the resulting ablation and thermal profiles. Sample problems showing the results of the ASCHAR analysis of a complete nozzle are given showing two-dimensional thermal effects.
- Rocket Engines