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Optimisation of a Rocket Nozzle Side Load Reduction Device

Stark, R. and Génin, Ch. (2012) Optimisation of a Rocket Nozzle Side Load Reduction Device. In: Proceedings. 48th AIAA Joint Propulsion Conference, 30. Jul. - 1. Aug 2012, Atlanta, GA, USA.

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The flow during transient startup and shutdown in all rocket engines operated on sea level under ambient conditions will separate inside the supersonic part of the nozzle. A separated nozzle flow is circumferential asymmetric distributed and induces high side loads. DLR carried out a cold flow subscale test campaign to study devices that can reduce the side loads during transient operation of a thrust optimised parabolic nozzle. A detailed parametrical study was performed and experimental data demonstrate the potential of the device to reduce the side loads.

Document Type:Conference or Workshop Item (Speech, Paper)
Title:Optimisation of a Rocket Nozzle Side Load Reduction Device
AuthorsInstitution or Email of Authors
Stark, R.Ralf.Stark@dlr.de
Génin, Ch.Chloe.Genin@dlr.de
Journal or Publication Title:Proceedings
Refereed publication:Yes
In ISI Web of Science:No
Keywords:nozzle flow, side loads, flow separation
Event Title:48th AIAA Joint Propulsion Conference
Event Location:Atlanta, GA, USA
Event Type:international Conference
Event Dates:30. Jul. - 1. Aug 2012
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Space
HGF - Program Themes:Space Transport
DLR - Research area:Raumfahrt
DLR - Program:R RP - Raumtransport
DLR - Research theme (Project):R - Antriebsystemtechnik - Schubkammertechnologie
Location: Lampoldshausen
Institutes and Institutions:Institute of Space Propulsion > Raketenantriebe
Deposited By: Chloe Nürnberger-Genin
Deposited On:08 Oct 2012 20:26
Last Modified:04 Nov 2012 09:40

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