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Experimental Study on Rocket Nozzle Side Load Reduction

Stark, Ralf and Génin, Ch. (2012) Experimental Study on Rocket Nozzle Side Load Reduction. Journal of Propulsion and Power, 28 (2), pp. 307-311. American Institute of Aeronautics and Astronautics (AIAA). doi: 10.2514/1.b34253. 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.

Item URL in elib:https://elib.dlr.de/77679/
Document Type:Article
Title:Experimental Study on Rocket Nozzle Side Load Reduction
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Stark, RalfUNSPECIFIEDhttps://orcid.org/0000-0003-1923-1901UNSPECIFIED
Date:March 2012
Journal or Publication Title:Journal of Propulsion and Power
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In ISI Web of Science:Yes
Page Range:pp. 307-311
Publisher:American Institute of Aeronautics and Astronautics (AIAA)
Keywords:nozzle flow, side loads, flow separation
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Space
HGF - Program Themes:Space Transportation
DLR - Research area:Raumfahrt
DLR - Program:R RP - Space Transportation
DLR - Research theme (Project):R - Antriebsystemtechnik - Schubkammertechnologie (old)
Location: Lampoldshausen
Institutes and Institutions:Institute of Space Propulsion > Rocket Propulsion
Deposited By: Nürnberger-Genin, Chloe
Deposited On:08 Oct 2012 20:28
Last Modified:29 Nov 2023 13:03

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