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

摘要

Challenge Project C2N is dedicated to developing and applying high performance computing capabilities to accelerate the development of hypergolic and hybrid rocket engine concepts. Computational fluid dynamics is employed to model chemically reacting flows within engine combustion chambers and computational chemistry is employed to characterize propellant physical and reactive properties. Accomplishments are presented and discussed.