The simulation of a class of three-dimensional, stationary, supersonic gas flows by construction of an approximate solution to the governing system of partial differential equations is analyzed. The investigated method is a hybrid one:it involves finite difference calculations on a regular, orthogonal grid, and characteristics calculations, the latter along the boundaries of the computational region. Alternative boundary treatment methods are studied for comparison.nThe convergence and stability properties of the used difference scheme are analyzed in depth and its dispersive and dissipative properties are examined in detail.
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