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Supersonic vortex plane and axisymmetric flows of non-viscousnon-heatconductive gas with arbitrary thermodynamic properties in the vicinityof a steady shock wave are studied. The differential equations describing thegas flow exterior to the discontinuity surface and the dynamic compatibilityconditions at this discontinuity are used. The gas flow nonuniformity in theshock vicinity is described by the space derivatives of the gasdynamicparameters at a point on the shock surface. The parameters are the gaspressure, density, velocity vector. The derivatives with respect to thedirections of the streamline and normal to it, and of the shock surface andnormal to it are considered. Space derivatives of all gasdynamic parameters areexpressed through the flow nonisobaric factor along the streamline, thestreamline curvature, and the flow vorticity and non-isoenthalpy factors. Analgorithm for these factors of the gas flow downstream a shock wavedetermination is developed. Examples of these factors calculation for imperfectoxygen and thermodynamically perfect gas are presented. The influencecoefficients of the upstream flow factors on the downstream flow factors arecalculated. As an illustration for flows with upstream Mach number 5 it isshown that the flow vorticity factor is the most influenced by thethermodynamical gas properties. The gas flow in the vicinity of the shock isdescribed by the isolines of gasdynamic parameters. Uniform plane andaxisymmetric flows on different distances from the axis of symmetry areexamined; the isobars, isopycnics, isotachs and isoclines are used tocharacterize the downstream flow behind a curved shock in an imperfect gas.

The flow gradients in the vicinity of a shock wave for a thermodynamically imperfect gas