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.
The influence of nozzle shape on the shock structure in separated flows / Nasuti, Francesco; Onofri, Marcello; E., Pietropaoli. - 563:563(2004), pp. 353-358. (Intervento presentato al convegno 5th European Symposium on Aerothermodynamics for Space Vehicles tenutosi a Cologne, GERMANY nel NOV 08-11, 2004).
The influence of nozzle shape on the shock structure in separated flows
NASUTI, Francesco;ONOFRI, Marcello;
2004
Abstract
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.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.
