Abstract
The flow conditions are represented by an oblique shock attached to the vertex of a straight edged wedge, placed symmetrically with respect to a uniform supersonic flow in front, so that the flow after the shcok is along the wedge surface. The curvature of the attached shock wave, and the flow variable gradients at the wedge tip caused by non-equilibrium vibrational effects are determined for a steady two-dimensional flow of a vibrationally relaxing gas. A relation between the curvature of the shock and that of the stream line is obtained at the wedge-tip. The variation of entropy and an expression for the vorticity generated by the shock towards down-stream flow are determined. Calculations have been carried out for the shock curvature and flow variable gradients for a wide range of wedge angle and the up-stream flow Mach number.
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