Title :
Combustion Chamber Fluid Dynamics and Hypergolic Gel Propellant Chemistry Simulations for Selectable Thrust Rocket Engines
Author :
Nusca, Michael J. ; McQuaid, Michael J.
Author_Institution :
Weapons & Mater. Directorate, US Army Res. Lab., Aberdeen, MD
Abstract :
This paper describes the development and application of high performance computing for the acceleration of tactical missile hypergolic propulsion system development. Computational fluid dynamics is employed to model the chemically reacting flow within a system´s 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 simulation; chemistry computing; computational fluid dynamics; flow simulation; gels; missiles; propulsion; rocket engines; chemically reacting flow; combustion chamber fluid dynamics; computational chemistry; computational fluid dynamics; high performance computing; hypergolic gel propellant chemistry simulations; propellant physical properties; propellant reactive properties; selectable thrust rocket engines; tactical missile hypergolic propulsion system development; Acceleration; Chemistry; Combustion; Computational modeling; Engines; Fluid dynamics; High performance computing; Missiles; Propulsion; Rockets;
Conference_Titel :
HPCMP Users Group Conference, 2006
Conference_Location :
Denver, CO
Print_ISBN :
0-7695-2797-3
DOI :
10.1109/HPCMP-UGC.2006.14
