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.


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    Title :

    Large-Eddy Simulation of a Generic Space Vehicle


    Contributors:


    Publication date :

    2008-01-01


    Size :

    17 pages





    Type of media :

    Article/Chapter (Book)


    Type of material :

    Electronic Resource


    Language :

    English




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