Vorticity on the Surface of an Axially Symmetric Body behind a Detached Shock Wave

The vorticity on the surface of an axially symmetric body streamlined by a steady unswirling homogeneous ideal gas supersonic flow with a detached shock wave has been studied. The formula for estimating the vorticity at any point on the body through its distance to the symmetry axis, the pressure at this point, the incident flow parameters, and the shock wave curvature radius at the point of its intersection with the symmetry axis has been derived. From this formula it follows that the vorticity on the surface of a body in axially symmetric flows differs from zero everywhere except for the point on the symmetry axis in contrast to two-dimensional symmetric flows.