Validation of the k – ω turbulence model for the thermal boundary layer profile of effusive cooled walls

Abstract

The choice of materials for rocket chamber walls is limited by its thermal resistance. The thermal loads can be reduced substantially by the blowing out of gases through a porous surface. The - based turbulence models for computational fluid dynamic (CFD) simulations are designed for smooth, non-permeable walls and have to be adjusted to account for the influence of injected fluids. Wilcox proposed therefore an extension for the - turbulence model for the correct prediction of turbulent boundary layer velocity profiles. In this study this extension is validated against experimental thermal boundary layer data from the Thermosciences Division of the Department of Mechanical Engineering from the Stanford University. All CFD simulations are performed with the finite volume based TAU code of the German Aerospace Center (DLR). Several simulations with different blowing settings were conducted and discussed in comparison to the results of the original model. Finally, the approach is applied to a two-dimensional simulation of an effusive cooled rocket chamber wall.