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

fYear

2006

fDate

26-29 June 2006

Firstpage

110

Lastpage

118

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;

fLanguage

English

Publisher

ieee

Conference_Titel

HPCMP Users Group Conference, 2006

Conference_Location

Denver, CO

Print_ISBN

0-7695-2797-3

Type

conf

DOI

10.1109/HPCMP-UGC.2006.14

Filename

4134042