The work addresses 3D supersonic flow over a stepped axisymmetric body with a nose cone. Dependencies of flow regimes on the angle of attack α and length L of the body part ahead of the step are studied. Experiments were conducted in the A-7 wind tunnel of the Research Institute of Mechanics, Moscow State University, at a free-stream Mach number of 3. The study reveals bands of the angle α and length L in which flow pressure on the leeward side of step increases with increasing α or L, and eventually it exceeds the pressure on the windward side. Numerical simulations are performed with a finite-volume solver on the basis of URANS equations. The supersonic flow structure at a given length L and angles of attack from 0 to 16°is scrutinized. The simulations unveil a supersonic jet propagating along the body leeward side. The jet is located between a pair of side vortices formed due to a development of the transversal flow separation. At α>5°and sufficiently large L, the supersonic jet impact creates a spot of anomalously high pressure on the leeward side of the step.