Theoretical investigation of three-dimensional shock wave-turbulent boundary layer interactions

The overall focus of the research effort is the understanding of the physical structure of 3-D shock wave-turbulent boundary layer interactions. The approach utilizes the full mean compressible Navier-Stokes equations with turbulence incorporated through the algebraic turbulent eddy viscosity model of Baldwin and Lomax. The research effort is categorized into two major areas. First, the efficacy of the Baldwin-Lomax model is examined for the 2-D supersonic compression ramp at Mach 3 and a Reynolds number based on upstream boundary layer thickness of 1.6 million. The results indicate that the Baldwin-Lomax model underestimates the upstream propagation of the shock-boundary layer interaction, and underestimates the recovery of the boundary layer downstream of reattachment. The incorporation of a simple relaxation modification to the eddy viscosity greatly improves the prediction of the upstream propagation, but does not appreciably affect the prediction of the downstream recovery of the boundary layer. Second, the three-dimensional interaction of an oblique shock wave with a turbulent boundary layer (the 3-D "sharp fin' configuration) at Mach 3 has been computed for two different shock strengths (i.e., shock-generator angles), and the results compared with the extensive experimental data. Present results indicate that the Baldwin-Lomax model provides an accurate prediction of a wide variety of flow properties, including surface pressure, heat transfer, yaw and pitch angle, static pressure and pitot pressure.