Accurate information on the heat transfer evolution along the hot gas wall of a rocket chamber is a crucial prerequisite for optimizing an engine's regenerative cooling circuit design. To improve Dasa's available data basis in this field, a calorimeter model combustor was developed and tested. The main objective of these experiments was to characterize the heat transfer behaviour of different co-axial injection element configurations under various operational conditions (P c : 100-=-120 bar, O/F: 6.0-^7.6) first without and then with gaseous hydrogen wall film cooling.The experimental results disclosed that the co-axial injection designs under investigation produce local wall heat loads that differ up to 25 percent. These differences in heat transfer become more apparent at axial distances of about 100 mm from the injector and beyond. An important finding was also that hydrogen wall film cooling employing the present slot injection principle is in fact much more effective when compared to wall element mixture ratio trimming under similar operational conditions.A major interest of the current program was finally, to apply Dasa's axisymmetric, Euler/Lagrange CFD-code CryoROC to the calorimeter chamber tests and assess its capability in this field. In doing so, it turned out that basically two parameters are sufficient to adapt the simulation to the experiment of interest, i.e. a characteristic droplet size distribution parameter, which mainly affects the axial build-up of the wall heat flux, and a global scaling factor for fine tuning of the observed wall heat flux level. The CryoROC results also demonstrated that a realistic simulation the wall heat transfer problem in a cryogenic rocket engine requires to * Senior Member AIAA

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