Ca. Schley et al., TOWARDS AN OPTIMAL CONCEPT FOR NUMERICAL CODES SIMULATING THRUST CHAMBER PROCESSES IN HIGH-PRESSURE CHEMICAL PROPULSION SYSTEMS, Aerospace science and technology, 1(3), 1997, pp. 203-213
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.