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Experiments on the shock wave/turbulent boundary layer interaction were conducted at the freestream Mach number M1e of 1.97 to 2.50 and the Reynolds number based on the boundary layerthickness Reδ1 of 3.1 x 10^4 to 5.8 x 10^4 using a supersonic nozzle having a divergent half angle of 10degrees. Nozzle wall static pressure measurements and the schlieren optical observation of theinteraction region were carried out. Also, the effects of M1e and Reδ1 on the shock-induced turbulentboundary layer separation were investigated theoretically. As a result, the analytical results of theratio Ps/P1 of the separation pressure Ps to the pressure at the onset of the interaction P1 were foundto increase with increasing M1e for a fixed Reδ1 and to increase with increasing Reδ1 for a fixed M1e and to provide excellent agreement with the experimental results on the shock-induced turbulentboundary layer separation

Shock-Induced Turbulent Boundary Layer Separation in Supersonic Nozzles.