Dr. R. Stark
The Flows Group works on research about modelling flows in the expansion nozzle of a rocket propulsion and modelling the reactive two-stage flow in the combustion chamber in experimental studies.
The expansion nozzles are investigated concerning their performance enhancement potential using altitude-adaptive and state of the art nozzle concepts, e.g. expansion-deflection and dual-bell nozzles. Another focal point of research are transient flow phenomena in the starting and shutting phase of the propulsions and the appearing asymmetric loads. To perform experiments we have access to the cold gas test facility P6.2 and specialised measurement technology to capture flow and structure dimensions.
Rocket combustion chambers exhibit turbulent reactive two-phase flows in the subcritical and supercritical pressure range of the liquids. As a consequence, the numeric simulation of these flows represents a major challenge. Our goal is a quantitative anticipation of the combustion process in the combustion chamber and the entailed thermal loads applied to the combustion chamber. These activities are integrated in the DLR project to drive forward and validate the TAU code for specific requirements in combustion chamber process simulation.