Parametric study of thermal behavior of thrust chamber cooling channels
A numerical investigation is adopted for two dimensional thermal analysis of rocket thrust chamber wall (RL10), employing finite difference model with iterative scheme (implemented under relaxation factor of 0.9 for convergence) to compute temperature distribution within thrust chamber wall (which...
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| Formato: | article |
| Lenguaje: | EN |
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Al-Khwarizmi College of Engineering – University of Baghdad
2007
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| Acceso en línea: | https://doaj.org/article/3742a048475c4ae592c03f2bf1da921a |
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