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...

Descripción completa

Guardado en:
Detalles Bibliográficos
Autor principal: Karima E. Amori
Formato: article
Lenguaje:EN
Publicado: Al-Khwarizmi College of Engineering – University of Baghdad 2007
Materias:
Acceso en línea:https://doaj.org/article/3742a048475c4ae592c03f2bf1da921a
Etiquetas: Agregar Etiqueta
Sin Etiquetas, Sea el primero en etiquetar este registro!