Combustion Chamber Fluid Dynamics and Hypergolic Gel Propellant Chemistry Simulations for Selectable Thrust Rocket Engines

Michael J. Nusca, Michael J. McQuaid
2006 2006 HPCMP Users Group Conference (HPCMP-UGC'06)  
orientation at which the fuel and oxidizer are injected. In conventional ISEs, the injectors point towards the This paper describes the application of high chamber's axial centerline while in the ISVE they are performance computing to accelerate the development of oriented so that (at least) initially, the fluids flow hypergolic propulsion systems for tactical missiles. tangential to the (radial) chamber wall. The ISVE is employed to model the orientation forces the propellants to mix in a
more » ... y coempualytion fl d ichi's cturbulent vortex region between the injector orifices and chemically reacting flow within a system 's combustion th came wls. Tre as loben oe chamber, and computational chemistry is employed to characterize propellant physical and reactive properties. experimental evidence that centrifugal forces act to Accomplishments from the past year are presented and separate the heavier solid particles from the gas particles discussed. and move them toward the chamber wall. These effects have two benefits. First, they promote an increase in the mixing path length, which enables better performance to
doi:10.1109/hpcmp-ugc.2006.14 fatcat:4ngfs7gqtrgobenhiz2kfvrts4