Volume 8, 2016Progress in Propulsion Physics
|Page(s)||95 - 116|
|Section||Liquid and electric space propulsion|
|Published online||06 July 2016|
Investigation of different modeling approaches for computational fluid dynamics simulation of high-pressure rocket combustors
Airbus Defence and Space Munich 81663, Germany
2 Deutsches Zentrum für Luft- und Raumfahrt (DLR) Institute of Aerodynamics and Flow Technology Göttingen 37073, Germany
The paper summarizes technical results and first highlights of the cooperation between DLR and Airbus Defence and Space (DS) within the work package “CFD Modeling of Combustion Chamber Processes” conducted in the frame of the Propulsion 2020 Project. Within the addressed work package, DLR Göttingen and Airbus DS Ottobrunn have identified several test cases where adequate test data are available and which can be used for proper validation of the computational fluid dynamics (CFD) tools. In this paper, the first test case, the Penn State chamber (RCM1), is discussed. Presenting the simulation results from three different tools, it is shown that the test case can be computed properly with steady-state Reynolds-averaged Navier-Stokes (RANS) approaches. The achieved simulation results reproduce the measured wall heat flux as an important validation parameter very well but also reveal some inconsistencies in the test data which are addressed in this paper.
© Owned by the authors, published by EDP Sciences, 2016
This is an Open Access article distributed under the terms of the Creative Commons Attribution License http://creativecommons.org/licenses/by/4.0, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.