EFFECT OF SHOCK CONTROL BUMPS ON OBLIQUE SHOCK WAVE TURBULENT BOUNDARY LAYER INTERACTIONS

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 therefore focused on techniques to mitigate the detrimental effects of such shock wave boundary layer interactions (SWBLI) and a variety of control strategies have been investigated. In this experimental study the effect of shock control bumps (SCBs) on oblique shock wave/boundary layer interactions is investigated, notably the influence of the position where the shock impinges with respect of the bump. The experiments are 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 x 103 and Mach number of 2. The effectiveness is assessed by looking at the size of the separated flow region, as well as the downstream boundary layer velocity profile. For this, stereo-PIV is employed as the main diagnostic method to characterise the three-dimensional flow field. In addition to this, high-speed Schlieren measurements are performed to asses the SCB performance, as well as the influence of the shock impingement location on the bump surface, on reducing the separation shock unsteadiness