Abstract
A new characteristic-based pressure-correction method designed for computation of flows at all speeds is presented. The method includes the implementation within the pressure-correction framework of interpolation of the characteristic variables, the approximation of the nonlinear operator by a stable segregate linear operator, the use of an approximate Riemann solver for the computation of the cell face inviscid flux, and the projection of the correction fields into the flux space. Application test cases include 1) supersonic inviscid arc bump flow, 2) transonic viscous double throat nozzle, and 3) incompressible lid driven cavity flow. The method is uniformly of high order and nonoscillatory, which leads to crisp shock representation without the creation of spurious oscillations. The results show a substantial improvement over existing pressure-correction methods for computation of compressible flows.
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