Numerical Analysis of Shock Diffraction over Rounded Corner

Shock wave motion is important in many areas of engineering like blast wave modeling, aeronautical design, medical applications, etc. Previous works mostly emphasized on sharp geometry responsible for flow separation immediately. In present study, shock diffraction over round corner is investigated solely and the intricate flow features are summarized. Numerical simulations are performed using Finite Volume Method. The rounded geometry requires laminar viscosity model due to continuous changes of the orientation. The unsteady flow field is designed to have an understanding appropriate to the test cases in real practice. Shear layer, vortex generation, secondary and recompression shock waves, etc. are clearly investigated. Induced flow velocity reaches supersonic level after being passed by the convergent-divergent passage and thereafter shocked to gets reduced in magnitude. Internal terminating shock compresses the flow to a relatively higher pressure to curve the shear layer in opposite direction. Beginning of separation and change in curvature of shear layer indicates more vortex strength than the primary vortex core.