TOWARDS AN OPTIMAL CONCEPT FOR NUMERICAL CODES SIMULATING THRUST CHAMBER PROCESSES IN HIGH-PRESSURE CHEMICAL PROPULSION SYSTEMS

Modelling aspects for rocker engines, where propellants are burned at high pressures to achieve a maximum of performance, are discussed. Con centrating on combustion chamber and expansion nozzle, critical flow p henomena are identified. Physical models for these phenomena with rega rd to numerical simulations are presented. Different numerical procedu res are analyzed concerning their advantages and disadvantages being a pplied for cryogenic high performance thrust chamber simulations. The application of some of these models is shown exemplarily for a 3D mult iinjector combustion chamber and the flowfield computation of a plug n ozzle concept to present capabilities, limitations and prospects of CF D in this area. Finally, remarks on verification of numerical schemes with regard to the individual physical, chemical and numerical models are given.