Abstract
An analytic method is presented to study the distribution of vorticity downstream the shock wave and the characteristics of the entropy layer for various cones and cylinders in supersonic flows. The relations of shock-shape, the distribution character of various parameters within the shock layer, and the entropy increment were combined to obtain the characteristics of vorticity and the entropy gradient. Numerical simulation are performed at the Mach number of 3, 5 and 10. The results indicate that the distribution of entropy and vorticity is connected with shock shape directly. Due to the differences of the shape of shock, the vorticity and the extreme value of entropy gradient for blunt-nosed cylinders are both larger than the cases for flat cylinders. As the shock-shape of flat-nosed cylinders is more liable to be affected than blunt-nosed cylinders with increasing Mach number, the position of the extreme value moves to the surface as the Mach number increases for flat-nosed cylinders, while it remains the identical value for blunt-nosed cylinders. The vorticity is regarded as the criterion of the edge of entropy layer in the normal direction, and two methods are proposed and discussed to estimate the edge.
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