The interaction of streamwise vortex with a shock wave

Experimental investigation of a longitudinal vortex/normal shock interaction is conducted at Mach numbers of 3, 4 and 6. The fields of total pressures in the core of a longitudinal vortex and its neighbourhood are obtained. The optical visualization of flow structure in an interaction region is executed. The strongly unsteady character of interaction process is detected. The numerical modeling of the streamwise vortex interaction with the oblique and normal shock wave was solved using three-dimension unsteady Euler and Navier - Stokes equations. Results of an experimental study of the region of interaction of a plane shock wave arising in the flow around a wedge and an axisymmetric shock wave formed by counterflow injection with a jet wake formed by co-current injection of gases (112, air, Ar). Three interaction modes are distinguished, depending on the gas- jet parameters: strong interaction with a subsonic velocity in the wake, moderate interaction with the formation of a subsonic flow region bounded by the shock wave whose shape is close to conical, and neutral interaction where the dynamic pressure in the jet is sufficient to overcome the pressure difference on the shock wave.