STRUCTURE OF CROSSING-SHOCK-WAVE TURBULENT-BOUNDARY-LAYER INTERACTIONS

A detailed comparison of experimental and computational results on the flowfield structure of a Mach 4, 15-deg symmetric crossing-shock-wave /turbulent-boundary-layer interaction is presented. Experimentally obt ained planar laser scattering images are compared with static-pressure contours predicted by the computation, with the computational results showing good overall agreement with the experimental data. The experi mental and computational results are used in a complementary manner to develop a detailed flowfield model of the crossing-shock interaction. The flowfield structure is found to consist of a complex shock struct ure overlying a large viscous separated region. This region occupies a significant portion of the outflow duct and consists of an accumulati on of low-Mach-number, low-stagnation-pressure fluid. This region may have significant implications for sidewall compression inlets.