7 TH EUROPEAN CONFERENCE FOR AERONAUTICS AND SPACE SCIENCES (EUCASS) Copyright  2017 by Wagner, et al. Published by the EUCASS association with permission. Rocket Propulsion in TAU: An Overview of the DLR ProTAU Project Bernd Wagner 1 Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR) - German Aerospace Center Institute of Space Propulsion, Management Lampoldshausen, 74239 Hardthausen, Germany Dirk Schneider; Scott Beinke; Dmitry Suslov; Chloé Génin; Justin Hardi; Michael Oschwald DLR, Institute of Space Propulsion, Rocket Propulsion Department Lampoldshausen, 74239 Hardthausen, Germany Eugeni Costa Ruiz DLR, Institute of Space Propulsion, Test Facility Technology Department Lampoldshausen, 74239 Hardthausen, Germany Sebastian Karl; Stefan Fechter; Daniel Banuti 2 ; Klaus Hannemann DLR, Institute of Aerodynamics and Flow Technology, Spacecraft Department Bunsenstr. 10, 37073 Göttingen, Germany Sebastian Jack; Marko Alder; Martin Rudolph 3 ; Thino Eggers DLR, Institute of Aerodynamics and Flow Technology, Spacecraft Department Lilienthalplatz 7, 38108 Braunschweig, Germany Peter Gerlinger; Markus Lempke 4 DLR, Institute of Combustion Technology, Numerical Simulation Department Pfaffenwaldring 38-40, 70569 Stuttgart, Germany Abstract The ProTAU project is an internal cooperation between several DLR institutes to advance the independent DLR expertise in modelling rocket propulsion systems and their components. The focus is on the development and validation of the DLR in-house CFD code TAU. The project began in early 2014 after an initial two-year phase of collaborative work between multiple DLR institutes. The project unifies the complementary code development, validation, simulation, and experimental work conducted by the various institutes. The collaboration facilitates a continuous exchange between developers and end-users allowing developers to respond more rapidly to user requirements and a more efficient development progress. In this paper, a brief overview of the ProTAU project structure is given. ProTAU is organized into four research topics: combustion chamber, nozzles, test facilities, and cooling. Highlights of the progress achieved will be shown for each main work package. 1 Corresponding author: Bernd.Wagner@dlr.de 2 Former employee of the Spacecraft Department - Göttingen 3 Former employee of the Spacecraft Department - Braunschweig 4 Former employee of the Numerical Simulation Department DOI: 10.13009/EUCASS2017-42