Topology of Shock-Wave/Boundary-Layer Interaction over Axisymmetric Bodies at Incidence

This computational study investigates the three-dimensional flow structure and aerodynamic characteristics of an impinging oblique shock wave interacting with a laminar boundary layer developing on an ogive–cylinder at [Formula: see text] and [Formula: see text] of approximately 35,800, with emphasis on angle-of-attack effects. At zero incidence, the interaction produces a highly three-dimensional open separation topology characterized by primary, secondary, and tertiary vortex systems. These vortices evolve downstream of the shock impingement region, leaving distinct surface signatures with saddle, focus, and nodal points. The shock-induced modification of freestream conditions generates crossflow away from the windward plane, resulting in complex momentum redistribution. The resulting aerodynamic loading includes strong negative lift and relatively small drag. At [Formula: see text], asymmetric shock strength and pressure gradients promote upstream separation on the upper surface, generating counter-rotating vortices, localized shock penetration, and altered surface pressure distributions. Although the vortex hierarchy remains similar to the zero-incidence case, the crossflow direction reverses across the interaction, fundamentally modifying vortex organization, surface topology, and momentum transport. The open separation topology changes from type I to type II at [Formula: see text]. These changes reduce the magnitude of negative lift while substantially increasing drag, demonstrating the strong influence of incidence on the separation dynamics and aerodynamic loading of three-dimensional axisymmetric shock-wave/boundary-layer interactions.