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Exhaust Shock Patterns Inside Over-Expanded Rocket Nozzles

Verma, S.B. and Ciezki, Helmut and Haidn, Oskar (2005) Exhaust Shock Patterns Inside Over-Expanded Rocket Nozzles. 25th Int. Symposium on Shock Waves, Bangalore (India).

Full text not available from this repository.

Abstract

An experimental study has been carried out to investigate the exhaust flow patterns from two types of rocket nozzles, each with a different expansion angle downstream of the last point of arc forming the throat. It is observed that this higher expansion angle results in the formation of an internal shock that influences the shock structure development considerably and also influences the side-load behavior in these nozzles significantly.

Item URL in elib:https://elib.dlr.de/50506/
Document Type:Conference or Workshop Item (Speech, Paper)
Title:Exhaust Shock Patterns Inside Over-Expanded Rocket Nozzles
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Verma, S.B.National Aerospace Laboratories, Bangalore, IndiaUNSPECIFIED
Ciezki, HelmutUNSPECIFIEDUNSPECIFIED
Haidn, OskarUNSPECIFIEDUNSPECIFIED
Date:July 2005
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Status:Published
Keywords:nozzle flow, shock structure, TIC nozzle, TOP nozzle
Event Title:25th Int. Symposium on Shock Waves
Event Location:Bangalore (India)
Event Type:international Conference
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: Ciezki, Dr.-Ing. Helmut
Deposited On:07 Aug 2007
Last Modified:27 Apr 2009 14:10

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