Asymmetric crossing shock wave-turbulent boundary layer interaction

Abstract

A collaborative experimental and theoretical study of the asymmetric crossing-shock- wave/turbulent-boundarylayer interaction is presented. The shock waves are generated by a pair of asymmetric fins that are mounted normal to a flat plate and form a converging channel. The focus of the study is the interaction of the shock waves with the turbulent boundary layer on the flat plate. Two configurations with fin angles 7 X 11 and 15 x 11 deg have been examined at Mach 3.9. Experimental data include surface pressure and heat transfer, adiabatic wall temperature, surface flow visualization, and planar laser scattering images. The computations solve the three-dimensional Reynolds-averaged compressible Navier-Stokes equations incorporating the two equation Chien k-e turbulence model. The computed surface pressure displays good agreement with experiment. The computed and experimental surface pressure and flowfield flow visualization are in general agreement. The computed surface heat transfer displays significant disagreement with experiment. The flowfield manifests a complex shock wave system and a pair of counter-rotating vortices.