DocumentCode
2731559
Title
Combustion Chamber Fluid Dynamics and Hypergolic Gel Propellant Chemistry Simulations for Selectable Thrust Rocket Engines
Author
Chen, Chiung-Chu ; Nusca, Michael J. ; Kotlar, Anthony J. ; McQuaid, Michael J.
Author_Institution
Weapons & Mater. Res. Directorate (ARL/WM-BD), US Army Res. Lab., Aberdeen Proving Ground, MD, USA
fYear
2009
fDate
15-18 June 2009
Firstpage
141
Lastpage
147
Abstract
Challenge Project C2N is dedicated to developing and applying high performance computing capabilities to accelerate the development of hypergolic and hybrid rocket engine concepts. Computational fluid dynamics is employed to model chemically reacting flows within engine combustion chambers and computational chemistry is employed to characterize propellant physical and reactive properties. Accomplishments are presented and discussed.
Keywords
chemically reactive flow; combustion; computational fluid dynamics; propellants; rocket engines; chemically reacting flows; combustion chamber; computational chemistry; computational fluid dynamics; hypergolic gel propellant chemistry simulations; selectable thrust rocket engines; Combustion; Computational fluid dynamics; Computational modeling; Engines; Fuels; Kinetic theory; Propulsion;
fLanguage
English
Publisher
ieee
Conference_Titel
DoD High Performance Computing Modernization Program Users Group Conference (HPCMP-UGC), 2009
Conference_Location
San Diego, CA
Print_ISBN
978-1-4244-5768-7
Type
conf
DOI
10.1109/HPCMP-UGC.2009.25
Filename
5729456
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