Abstract
The flow field for thermal stage separation is carried out and predicted by unsteady numerical simulation with the dynamic moving grids in this work. The overset grids are applied to simulate the relative separating motion of multi-stage rocket. The flow problems and effects of different exhaust holes within the interstage under considering the design of thermal stage separation are systematically computed, discussed and also analyzed. © 2009 Elsevier Ltd. All rights reserved.
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Shieh, T. H., Liou, T. M., Li, M. R., Liu, C. H., & Wu, W. J. (2009). Analysis on numerical results for stage separation with different exhaust holes. International Communications in Heat and Mass Transfer, 36(4), 342–345. https://doi.org/10.1016/j.icheatmasstransfer.2009.01.011
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