Supersonic Flow Over a Cylindrical Protrusion With Vortex Generator

Supersonic flow around the cylindrical protrusion can cause a bow shock, which interacts with the incoming flow boundary layer. Such shock wave - boundary layer interaction can lead to a complex flow phenomenon, which increase the aerodynamic drag and also causes the flow unsteadiness. It is essentially more important to reduce the drag and flow unsteadiness by approaching a control technique against the interaction between the shock wave induced by a protrusion and wall boundary layer. In the present work, the control of shock wave boundary layer interaction by a ramp type vortex generator is investigated using unsteady RANS methodology. Vortex generator was placed ahead of cylindrical protrusion into the supersonic stream of Mach number 2.0. The flow fields around the cylindrical protrusion from the present numerical results are compared with the experimental result for steady pressure data. Adopting vortex generator can helps in reduction of surface pressure fluctuation. The frequency spectra for the cylindrical protrusion with vortex generator showed greatly reduced spectral density values, and collapse faster than the case without vortex generator.