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Experimental study of boundary layer separation in truncated ideal contour nozzles

Stark, Ralf and Wagner, Bernd (2008) Experimental study of boundary layer separation in truncated ideal contour nozzles. Shock Waves. Springer Berlin / Heidelberg. DOI: 10.1007/s00193-008-0174-6 ISSN 0938-1287 (Print) 1432-2153 (Online)

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Official URL: http://www.springer.com/engineering/mechanical+eng/journal/193


DLR Lampoldshausen carried out a cold flow test series to study the boundary layer separation and the related flow field in a truncated ideal contour nozzle. A special focus was set on low nozzle pressure ratios to identify the origin of a locally re-attached flow condition that was detected in previous test campaigns. A convex shaped Mach disc was found for nozzle pressure ratios less than 10 and a slight concave one for nozzle pressure ratios more than 20. Due to boundary layer transition at low nozzle pressure ratios the convex Mach disc is temporary tilted and redirects the flow towards the nozzle wall. A simple separation criterion for turbulent nozzle flows is presented that fits well for both cold and hot flows. It is shown that the oblique separation shock recompresses the flow to 90% of the ambience. The separation zone of the presented film cooled nozzle is compared with a conventional one around 40% longer. Furthermore a relation between shear layer shape and forced side loads is described.

Item URL in elib:https://elib.dlr.de/57195/
Document Type:Article
Title:Experimental study of boundary layer separation in truncated ideal contour nozzles
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Date:7 November 2008
Journal or Publication Title:Shock Waves
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In ISI Web of Science:Yes
DOI :10.1007/s00193-008-0174-6
Publisher:Springer Berlin / Heidelberg
ISSN:0938-1287 (Print) 1432-2153 (Online)
Keywords:Flow separation, Ideal contour nozzles, Side loads, Mach disc, Separation criteria
HGF - Research field:Aeronautics, Space and Transport (old)
HGF - Program:Space (old)
HGF - Program Themes:W RP - Raumtransport
DLR - Research area:Space
DLR - Program:W RP - Raumtransport
DLR - Research theme (Project):W - Antriebsystemtechnik - Schubkammertechnologie und Hochdruckverbrennung (old)
Location: Lampoldshausen
Institutes and Institutions:Institute of Space Propulsion > Technologie
Deposited By: Stark, Dr.-Ing. Ralf
Deposited On:11 Jan 2009
Last Modified:27 Apr 2009 15:40

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