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H2/O2 Rocket Combustor Flow Field Modeling, Simulation and Analysis.

Schweitzer, C. and Schley, C.-A. (1997) H2/O2 Rocket Combustor Flow Field Modeling, Simulation and Analysis. In: 33rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Seattle, WA, July 7-9, 1997.

Full text not available from this repository.


Item URL in elib:https://elib.dlr.de/25088/
Document Type:Conference or Workshop Item (Paper)
Additional Information: LIDO-Berichtsjahr=1997, pages=20,
Title:H2/O2 Rocket Combustor Flow Field Modeling, Simulation and Analysis.
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Schweitzer, C.UNSPECIFIEDUNSPECIFIED
Schley, C.-A.UNSPECIFIEDUNSPECIFIED
Date:1997
Journal or Publication Title:33rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Seattle, WA, July 7-9, 1997
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Series Name:AIAA 97-3300
Status:Published
Keywords:H2/O2, Rocket Combustor, Rocket engine,
HGF - Research field:UNSPECIFIED
HGF - Program:Space (old)
HGF - Program Themes:W RP - Raumtransport
DLR - Research area:UNSPECIFIED
DLR - Program:W RP - Raumtransport
DLR - Research theme (Project):E - no assignment
Location: Lampoldshausen
Institutes and Institutions:Institute of Space Propulsion
Deposited By: DLR-Beauftragter, elib
Deposited On:02 Apr 2006
Last Modified:27 Apr 2009 05:42

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