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.