CFD Simulation of Chemical Non‐Equilibrium Reacting Flow within the AHRES Hybrid Rocket Engine

Kurzfassung

Within this study, the flow and the combustion process inside the reaction chamber of the AHRES engine is discussed based on several 2D and 3D steady-state simulations carried out with the DLR flow solver TAU. The computed engine is a lab-scale hybrid rocket engine for ground tests, operated by the DLR - Institute of Aerodynamics and Flow Technology in the project ATEK. It is propelled with hydrogen peroxide as oxidizer and HTPB with different additives as fuel. A first comparison of numerical simulation and ground test results is realized and shows good agreements with globally measured values.