LES of shock wave / turbulent boundary layer interaction

Simulation method
exact filtered shock solution, where the high-wavenumber part of the
spectrum has been removed, is slightly oscillatory owing to the Gibbs
phenomenon.
2.4 Boundary conditions
Boundary data are imposed as follows. At inflow we prescribe all conservative
variables f as function of time, using data from a separate
computation. For the compression corner calculation results of a flat
plate boundary layer calculation are used. This calculation in turn supplies
inflow conditions for the decompression corner. The rescaling and
recycling method of Stolz & Adams (2003) is employed for the flat plate
simulation, see section 3 for a discussion. Periodic boundary conditions
were applied in the spanwise direction. At the outflow a sponge-layer
technique is used (Adams, 1998). At the upper truncation plane of the
computational domain non-reflecting conditions are imposed. The wall
is assumed to be isothermal and no-slip conditions are enforced on the
velocity. The wall-temperature distribution is uniform in spanwise direction,
along the streamwise direction it is taken from the experiment
of Zheltovodov et al. (1987), where the wall is supposed to be adiabatic.
Since in this experiment the non-dimensional wall temperature on the
flat plate has a small difference compared to that of the considered case,
it was rescaled linearly. Then the data was smoothed and interpolated
onto the computational grid as shown in figure 2.3. Isothermal conditions
are preferable over adiabatic conditions since for the experiment an
almost constant temperature distribution in time was observed during
the measurements.