DocumentCode
2421669
Title
Combustion Chamber Fluid Dynamics and Hypergolic Gel Propellant Chemistry Simulations for Selectable Thrust Rocket Engines
Author
Nusca, Michael J. ; Chen, Chiung-Chu ; McQuaid, Michael J.
Author_Institution
Weapons & Mater. Res. Directorate, US Army Res. Lab., Aberdeen, MD
fYear
2008
fDate
14-17 July 2008
Firstpage
103
Lastpage
108
Abstract
This paper describes the application of high performance computing to accelerate the development of hypergolic propulsion systems for tactical missiles. Computational fluid dynamics is employed to model the chemically reacting flow within a systempsilas combustion chamber, and computational chemistry is employed to characterize propellant physical and reactive properties. Accomplishments from the past year are presented and discussed.
Keywords
aerospace propulsion; chemically reactive flow; combustion; computational fluid dynamics; defence industry; missiles; propellants; rocket engines; CFD; chemically reacting flow; combustion chamber fluid dynamics; computational fluid dynamics; hypergolic gel propellant chemistry simulations; hypergolic propulsion systems; tactical missiles; thrust rocket engines; Acceleration; Chemistry; Combustion; Computational modeling; Engines; Fluid dynamics; High performance computing; Missiles; Propulsion; Rockets;
fLanguage
English
Publisher
ieee
Conference_Titel
DoD HPCMP Users Group Conference, 2008. DOD HPCMP UGC
Conference_Location
Seattle, WA
Print_ISBN
978-1-4244-3323-0
Type
conf
DOI
10.1109/DoD.HPCMP.UGC.2008.28
Filename
4755850
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