Investigation on Heat Transfer and Injector Design Criteria for Methane/Oxygen Rocket Combustion Chambers

The expansion of the space launcher market increased the need for reliable high-performance rocket engines, which have to be also cost-effective. For this reason, new fuel combinations have been intensively investigated worldwide. Due to its many advantages i. e. high performance and good cooling properties, methane/oxygen has been recently considerded as new rocket propellants combination. This work contributes to increase the level of knowledge concerning injection and combustion processes in single- and multi-element rocket combustion chambers. The goal of these efforts has been to provide sufficient information for designing reliable high-performance injectors and to provide a detailed experimental database in oxygen-methane domain.