Summary
A method for simulations of the compressible flow in aerodynamically highly loaded turbomachines on unstructured adaptive grids is presented. The discretization of the conservation laws in space is executed by the finite volume method. For high efficiency an implicit solution procedure is used. The flux vector of the inviscid flow is calculated by a modified difference splitting method described by Reichert and Simon [9]. The generation of the initial grid and the grid adaptation are executed with the advancing-front method according to Peraire et al. [14] creating a grid consisting of triangles. The grid adaptation is based on an error estimation. In the case of turbulent flows, quadrilateral grid elements are also used for the efficient resolution of boundary layers. Examples are presented for inviscid and viscous subsonic and transonic flows. A test case for supersonic flow is described in [11].
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© 1996 Friedr. Vieweg & Sohn Verlagsgesellschaft mbH, Braunschweig/Wiesbaden
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Roehl, C., Simon, H. (1996). Flow Simulations in Aerodynamically Highly Loaded Turbomachines Using Unstructured Adaptive Grids. In: Hirschel, E.H. (eds) Flow Simulation with High-Performance Computers II. Notes on Numerical Fluid Mechanics (NNFM), vol 48. Vieweg+Teubner Verlag. https://doi.org/10.1007/978-3-322-89849-4_32
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DOI: https://doi.org/10.1007/978-3-322-89849-4_32
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