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Experimental Study on Rocket Nozzle Side Load Reduction

Stark, R. and Génin, Ch. (2012) Experimental Study on Rocket Nozzle Side Load Reduction. Journal of Propulsion and Power, 28 (2), pp. 307-311. ISSN 0748-4658.

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The flow in all rocket engines operated on sea level under ambient conditions will separate inside the supersonic part of the nozzle during transient startup and shutdown. A separated nozzle flow has an asymmetrical distribution in the circumferential direction and therefore induces high side loads. The German Aerospace Center of Lampoldshausen carried out a cold flow subscale test campaign to study devices that can reduce the side loads during transient engine operation. These devices can be installed on either ground test facilities or launch pads. A detailed parametric study was performed, and experimental data demonstrate the potential of the device for side load reduction.

Document Type:Article
Title:Experimental Study on Rocket Nozzle Side Load Reduction
AuthorsInstitution or Email of Authors
Stark, R.Ralf.Stark@dlr.de
Génin, Ch.Chloe.Genin@dlr.de
Date:March 2012
Journal or Publication Title:Journal of Propulsion and Power
Refereed publication:Yes
In Open Access:No
In ISI Web of Science:Yes
Page Range:pp. 307-311
Keywords:nozzle flow, side loads, flow separation
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 20:28
Last Modified:07 Feb 2013 20:34

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