3-d crossing shock wave-turbulent boundary layer interaction

A computational study of the crossing shock waveturbulent boundary layer interaction is presented. The shock waves are generated by a pair of fins which are mounted normal to a flat plate and form a converging channel. The focus of the study is to investigate the ability of modified k – ∈ turbulence model to predict the the interaction of the shock waves with the turbulent boundary layer on the flat plate. Three configurations with fin angles of 7° × 7°, 7° × 11° and 15° × 15° have been examined at Mach 3.9. Experimental data includes surface pressure, heat transfer, adiabatic wall temperature and surface flow visualization. Computations solve the 3-D Reynolds-averaged compressible Navier-Stokes equations incorporating the new low Reynolds number correction of Knight to the two equation k–∈ turbulence model. The computed surface pressure displays good agreement with experiment. The computed adiabatic wall temperature exhibits excellent agreement with experiment. The computed and experimental surface and flowfield flow visualization are in general agreement. The computed surface heat transfer displays significant disagreement with experiment for the stronger interaction. The flowfield manifests a complex shock wave system, and a pair of counter-rotating vortices.