The Influence of Nozzle Shape on the Shock Structure in Separated Flows

Details The Influence of Nozzle Shape on the Shock Structure in Separated Flows The Influence of Nozzle Shape on the Shock Structure in Separated Flows

Feb 2005

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2005esasp.563..353n&link_type=abstract

Proceedings of the Fifth European Symposium on Aerothermodynamics for Space Vehicles (ESA SP-563). 8-11 November 2004, Cologne,

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The performance of liquid rocket engines is presently limited by the side loads that take place during the startup because of the coupling between the natural flow asymmetry and a peculiar shock structure inside the nozzle. The shock and flow structures of highly overexpandend nozzles are examined numerically, with a critical discussion on the reasons yielding the different possible configurations. The results confirm that a major role is played by the flow gradients ahead of the shock and thus by the nozzle geometry. Key words: Nozzle; Flow separation; Mach reflection.

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