Summary
For ideal nozzles, basically two different types of shock structures in the plume may appear for overexpanded flow conditions, a regular shock reflection or a Mach reflection at the nozzle centreline. Especially for rocket propulsion, other nozzle types besides the ideal nozzles are often used, including simple conical, thrust-optimized or parabolic contoured nozzles. Depending on the contour type, another shock structure may appear: the so-called cap-shock pattern. The exact knowledge of the plume pattern is of importance for mastering the engine operation featuring uncontrolled flow separation inside the nozzle, appearing during engine start-up and shut-down operation. As consequence of uncontrolled flow separation, lateral loads may be induced. The sideload character strongly depends on the nozzle design, and is a key dimensional load for the nozzle’s mechanical structure. It is shown especially for the VULCAIN and VULCAIN 2 nozzle, how specific shock pattern evolve during transients, and how - by the nozzle design - undesired flow phenomena can be avoided.
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© 2009 Springer-Verlag Berlin Heidelberg
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Hagemann, G. (2009). Shock pattern in the plume of rocket nozzles - needs for design consideration. In: Hannemann, K., Seiler, F. (eds) Shock Waves. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-540-85168-4_8
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DOI: https://doi.org/10.1007/978-3-540-85168-4_8
Publisher Name: Springer, Berlin, Heidelberg
Print ISBN: 978-3-540-85167-7
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