Investigation of shock control bump geometry variation on oblique shock wave boundary layer interactions
More Info
expand_more
Abstract
The interaction between a shock wave and a boundary layer is a topic of primary relevance in high-speed aerodynamics, as it may deteriorate the vehicle performance, and can even lead to structural damage. Over the years, many researchers have investigated various control techniques to mitigate the detrimental effects of such shock wave boundary layer interactions (SWBLI). In this experimental study the effect of shock control bumps (SCB) on oblique shock wave/boundary layer interactions is investigated, notably the influence of the ramp section of the bump. To study the effect, varying bump geometries were designed with 5 different ramp angles while the maximum crest height is kept constant. The experiments were conducted in the ST-15 wind-tunnel at the Delft University of Technology for fully developed turbulent boundary layer conditions with Reθ of 21.8 103 and freestream Mach number of 2.0. The effectiveness is assessed from the size of the separated flow region, as well as the downstream boundary layer velocity profile. For this, PIV is employed as the main diagnostic method to characterise the flow field. In addition to this, high-speed Schlieren and oil flow measurements were performed to asses the effect of the SCB on the overall interaction structure.