Abstract
With the ever rising demands for cheaper payload delivery to orbit, dual bell nozzle with a potential theoretical performance gain of up to 10% can represents one of the major ways of advance to achieve the goal. The well-known transition unsteadiness in a dual-bell rocket nozzle represents one of the major concerns for the development of such altitude compensating type nozzle (ACN). The present study proposes and investigates the possibilities of secondary radial injection for flow regime transition control. Present experimental results demonstrate potential effects of secondary injection on transition and re-transition control even with a relatively low secondary injection mass flow rates. Doing so, the transition and retransition process were significantly delayed towards the ideal transition point. In addition, side loads have been found to be greatly decreased or even eliminated.
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[a From Hagemann et al. (1998)]
(From Hagemann et al. 1998)
(b From Zmijanovic et al. 2018)
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Acknowledgements
We would like to gratefully acknowledge the laboratory of Excellence CAPRYSSES framework and the financial support of this study from Grant No. ANR-11-LABX-0006-01 of the Investissements d’Avenir LabEx CAPRYSSES. We would also like to thank Nicolas Gouillon for his technical assistance and Matthieu Sammut for his assistance during patent filing.
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Léger, L., Zmijanovic, V., Sellam, M. et al. Controlled flow regime transition in a dual bell nozzle by secondary radial injection. Exp Fluids 61, 246 (2020). https://doi.org/10.1007/s00348-020-03086-3
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DOI: https://doi.org/10.1007/s00348-020-03086-3