Towards an optimal concept for numerical codes simulating thrust chamber processes in high pressure chemical propulsion systems

Modelling aspects for rocket engines, where propellants are burned at high pressures to achieve a maximum of performance, are discussed. Concentrating on combustion chamber and expansion nozzle, critical flow phenomena are identified. Physical models for these phenomena with regard to numerical simulations are presented. Different numerical procedures are analyzed concerning their advantages and disadvantages being applied for cryogenic high performance thrust chamber simulations. The application of some of these models is shown exemplarily for a 3D multiinjector combustion chamber and the flowfield computation of a plug nozzle concept to present capabilities, limitations and prospects of CFD in this area. Finally, remarks on verification of numerical schemes with regard to the individual physical, chemical and numerical models are given.