Separation length scaling for dual-incident shock wave-turbulent boundary layer interactions with different shock wave distances

In this study, the length scaling for the boundary layer separation induced by two incident shock waves is experimentally and analytically investigated. The experiments are performed in a Mach 2.73 flow. A double-wedge shock generator with two deflection angles (alpha(1) and alpha(2)) is employed to generate two incident shock waves. Two deflection angle combinations with an identical total deflection angle are adopted: (alpha(1) = 7 degrees, alpha(2) = 5 degrees) and (alpha(1) = 5 degrees, alpha(2) = 7 degrees). For each deflection angle combination, the flow features of the dual-incident shock wave-turbulent boundary layer interactions (dual-ISWTBLIs) under five shock wave distance conditions are examined via schlieren photography, wall-pressure measurements and surface oil-flow visualisation. The experimental results show that the separation point moves downstream with increasing shock wave distance (d). For the dual-ISWTBLIs exhibiting a coupling separation state, the upstream interaction length (L-int) of the separation region approximately linearly decreases with increasing d, and the decrease rate of Lint with d increases with the second deflection angle under the condition of an identical total deflection angle. Based on control volume analysis of mass and momentum conservations, the relation between L-int and d is analytically determined to be approximately linear for the dual-ISWTBLIs with a coupling separation region, and the slope of the linear relation obtained analytically agrees well with that obtained experimentally. Furthermore, a prediction method for Lint of the dual-ISWTBLIs with a coupling separation region is proposed, and the relative error of the predicted Lint in comparison with the experimental result is similar to 10 %.

Automated summary

This study experimentally and analytically investigates the length scaling for the boundary layer separation induced by two incident shock waves in a Mach 2.73 flow. The experimental results show that the separation point moves downstream with increasing shock wave distance. For the dual-incident shock wave-turbulent boundary layer interactions exhibiting a coupling separation state, the upstream interaction length approximately linearly decreases with increasing distance, and the decrease rate increases with the second deflection angle. A prediction method for the upstream interaction length is proposed, with a relative error of about 10% compared to the experimental result.