Shock-Induced Turbulent Boundary Layer Separation in Supersonic Nozzles

Abstract

Experiments on the shock wave/turbulent boundary layer interaction were conducted at the free stream Mach number M_1e of 1.97 to 2.50 and the Reynolds number based on the boundary layer thickness Re_δ1 of 3.1×10⁴ to 5.8×10⁴ using a supersonic nozzle having a divergent half angle of 10 degrees. Nozzle wall static pressure measurements and the schlieren optical observation of the interaction region were carried out. Also, the effects of M_1e and Re_δ1 on the shock-induced turbulent boundary layer separation were investigated theoretically. As a result, the analytical results of the ratio p_s/p₁ of the separation pressure p_s to the pressure at the onset of the interaction p₁ were found to increase with increasing M_1e for a fixed Re_δ1 and to increase with increasing Re_δ1 for a fixed M_1e and to provide excellent agreement with the experimental results on the shock-induced turbulent boundary layer separation.