<DOC>
<DOCNO>
256
</DOCNO>
<TITLE>
an experimental study of the glancing interaction between
a shock wave and a turbulent boundary layer .
</TITLE>
<AUTHOR>
stanbrook,a.
</AUTHOR>
<BIBLIO>
arc cp.555, 1960.
</BIBLIO>
<TEXT>
  an experimental study has been made at mach numbers from 1.6 to 2.0 of
the interaction between the turbulent
boundary layer on a side wall of a wind
tunnel and the shock wave produced by
a plate mounted on the wall .  under
these conditions the shock wave boundary
layer interaction was three
dimensional at least over the region
investigated (up to 10 boundary layer
thicknesses from the plate) .  it was
found that the boundary layer was separated
by a shock wave of strength
type occur on the sides of fuselages at
the wing fuselage junction and may
therefore be important with regard to the
design of waisted shapes .
</TEXT>
</DOC>
