Volume 5, Juin 2013Progress in Flight Physics
|Page(s)||169 - 190|
|Section||Chapter Four. Vortex, wake, and base flows|
|Published online||14 June 2013|
Base-flow sensitivity of a generic rocket forebody towards small freestream angles
Institute of Aeronautics and Astronautics, RWTH Aachen 7
2 Institute of Aerodynamics and Flow Technology German Aerospace Center (DLR) 7 Lilienthalplatz, Braunschweig 38108, Germany 10 Bunsenstraße, Göttingen 37073, Germany
Experimental and numerical investigations have been conducted regarding the wake flow of a generic rocket model in subsonic freestream conditions. The bluff base geometry evokes a recirculation area represented by counterrotating vortices. Experiments using Particle Image Velocimetry (PIV) demonstrate that the spatial organization of this area is heavily dependent on small freestream angles (α, β < 1°), associated with a significant shift in the base pressure distribution. Numerical studies using Reynolds-Averaged Navier-Stokes (RANS) methods with one- and twoequation turbulence models are able to predict the mean velocity field as well as tendencies regarding α and β, but lack the sensitivity of the experiments. The mean pressure level on the base is calculated within 10% of the experimental value using the two-equation turbulence model, although the pressure distributions on the base show distinct differences.
© Owned by the authors, published by EDP Sciences, 2013
This is an Open Access article distributed under the terms of the Creative Commons Attribution License 2.0, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.