Numerical Simulation of Cryogenic Injection in Rocket Engine Combustion Chambers

The numerical simulation of cryogenic combustion is crucial for a better understanding of the complex physics involved in reactive flows of rocket engines and to help to reduce the development cost of these engines. The focus of this study is set on the oxidizer injection and its dispersion through jet dense core destabilization and atomization or supercritical mixing. Specific models have been implemented in the CFD code CEDRE created by ONERA to address these physical phenomena.