Numerical investigation of active control of shock wave/boundary layer interaction

In this study, we have applied the Navier—Stokes equations and Reynolds stress model (RSM) in the Fluent Software so as to investigate physics of flow on a compression expansion ramp with an angle of 25° subjected to 3D shock wavefboundary layer interaction. Shadowgraph contours, which visibly illustrate shock wave structures, were used to find fine flow structures. A comparison was made between the data from Zeltovodov et al. (1990) and the obtained results at the same conditions of geometry, boundary conditions, etc. This comparison reveals good agreement of results with experimental data of wall pressure distribution. Moreover, we investigated the influence of suction and blowing active control methods on shock structure. The results show that use of suction has changed flow structure particularly in the vicinity of the ramp in a way thatat all mass flow rates no shock waves attached to the ramp are observed. Also, with decrease in suction rate the separated oblique shock occurs sooner and moves to the left. The strength of the emerged oblique shock has not experienced a considerable change with change in suction rate and Mach distribution has almost remained constant. Furthermore, increase in blowing rate brings about a reduction in oblique shock wave strength.