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This paper presents a numerical study of the plume flow field in a nine-nozzle liquid rocket configuration, focusing on the complex interactions and phenomena occurring during ascent. The study establishes an analytical model and verifies its reliability through comparisons with wind tunnel test data, revealing significant jet collisions and flow diversions at various altitudes. The findings aim to enhance the understanding of thermal environments for multi-nozzle rockets, providing insights for future ther
- Author
- Durga Sravan
- Language
- EN