The supersonic flow past the blunt base of an axisymmetric aerodynamic body is of fundamental importance for any rocket-like configuration, since these bodies often suffer from high base drag. This work deals with the investigation of the base flow of a cylindrical rocket configuration using large-eddy simulations. In this a system of three vortices in the base region was found to have a major influence on the flow characteristic such as an according decomposition of the pressure on the nozzle wall as well as an upstream directed transport of the hot exhaust gas. A Fourier analysis of the pressure distribution shows a highly time-dependent character of the baseflow and its connection with the interaction of the nozzle flow with the outer flow field. As a prove of the reliability of the used numerical method a comparison with experimental data was carried out showing a good qualitative agreement between the experimental and numerical data.
Large-Eddy Simulation of a Generic Space Vehicle
2008-01-01
17 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
Large-Eddy Simulation of the Base Flow of a Cylindrical Space Vehicle Configuration
British Library Conference Proceedings | 2009
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