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

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 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.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Jun 01, 2007
Accession Number
ADP023761

Entities

People

  • Chiung-chu Chen
  • Michael J. McQuaid
  • Michael J. Nusca

Organizations

  • United States Army Research Laboratory

Tags

Communities of Interest

  • Biomedical
  • Counter WMD
  • Energy and Power Technologies
  • Weapons Technologies

DTIC Thesaurus Topics

  • Chemical Reaction Properties
  • Chemical Reactions
  • Chemistry
  • Combustion
  • Combustion Chambers
  • Computational Fluid Dynamics
  • Department Of Defense
  • Fluid Dynamics
  • High Performance Computing
  • High Pressure
  • Materials Science
  • Propellants
  • Propulsion Systems
  • Reaction Mechanisms
  • Recombination Reactions
  • Rocket Engines
  • Rocket Oxidizers

Fields of Study

  • Physics

Readers

  • Aerospace Test and Evaluation
  • Internal Combustion Engine (ICE) Technology.
  • Quantum Chemistry