NDLI: Shock pattern in the plume of rocket nozzles: needs for design consideration

Content Provider	Springer Nature Link
Author	Frey, Manuel Hagemann, Gerald
Copyright Year	2008
Abstract	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 side-load character strongly depends on the nozzle design, and is a key feature for the nozzle’s mechanical structure layout. It is shown especially for the VULCAIN and VULCAIN 2 nozzle, how specific shock patterns evolve during transients, and how - by the nozzle design - undesired flow phenomena can be avoided.
Ending Page	395
Page Count	9
Starting Page	387
File Format	PDF
ISSN	09381287
e-ISSN	14322153
Journal	Shock Waves
Issue Number	6
Volume Number	17
Language	English
Publisher	Springer-Verlag
Publisher Date	2008-04-01
Publisher Place	Berlin, Heidelberg
Access Restriction	One Nation One Subscription (ONOS)
Subject Keyword	Thermodynamics Fluids Shock shock interaction Rocket engine Engineering Thermodynamics, Transport Phenomena Condensed Matter Engineering Fluid Dynamics Rocket nozzle Acoustics Shock wave
Content Type	Text
Resource Type	Article
Subject	Physics and Astronomy Mechanical Engineering

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