Numerical Investigation of the Effect of Pressure Ratio on the Shock Boundary Layer Interaction in a duct with Constant Cross-Section

The present research is mainly devoted to investigate the effect of pressure ratio (ᴨ) on the Shock Wave-Boundary Layer interaction phenomena along the wall surface in internal compressible flows. The implicit Reynolds Average Navier-Stokes equations and k-ω turbulent model have been used to numerical simulation and investigation the effect of pressure ratio on location, structure of the shock train and the boundary layer specification. The obtained results show that the present numerical results are in good agreement with the experimental data. On increasing ᴨ, not only the shock train moved toward the upstream flow but also the shock structure changed from X-shape to λ. Furthermore with increasing ᴨ the displacement of shock train along the duct is increased. With decreasing ᴨ the shock train moved to the downstream so that the length of the duct isn’t enough for complete recovery pressure. The flow separation bubble is formed near the wall, when the shock was strong. The experimental results of supersonic blow down wind tunnel in Cambridge University have been used for validation.