  The interaction between an incident shock wave and a Mach-6 undisturbed
hypersonic laminar boundary layer over a cold wall is addressed using direct
numerical simulations (DNS) and wall-modeled large-eddy simulations (WMLES) at
different angles of incidence. At sufficiently high shock-incidence angles, the
boundary layer transitions to turbulence via breakdown of near-wall streaks
shortly downstream of the shock impingement, without the need of any inflow
free-stream disturbances. The transition causes a localized significant
increase in the Stanton number and skin-friction coefficient, with high
incidence angles augmenting the peak thermomechanical loads in an approximately
linear way. Statistical analyses of the boundary layer downstream of the
interaction for each case are provided that quantify streamwise spatial
variations of the Reynolds analogy factors and indicate a breakdown of the
Morkovin's hypothesis near the wall, where velocity and temperature become
correlated. A modified strong Reynolds analogy with a fixed turbulent Prandtl
number is observed to perform best. Conventional transformations fail at
collapsing the mean velocity profiles on the incompressible log law. The WMLES
prompts transition and peak heating, delays separation, and advances
reattachment, thereby shortening the separation bubble. When the shock leads to
transition, WMLES provides predictions of DNS peak thermomechanical loads
within $\pm 10\%$ at a computational cost lower than DNS by two orders of
magnitude. Downstream of the interaction, in the turbulent boundary layer,
WMLES agrees well with DNS results for the Reynolds analogy factor, the mean
profiles of velocity and temperature, including the temperature peak, and the
temperature/velocity correlation.
