<DOC>
<DOCNO>
630
</DOCNO>
<TITLE>
stagnation region in rarefied high mach number flow .
</TITLE>
<AUTHOR>
cheng,h.k. and chang,a.l.
</AUTHOR>
<BIBLIO>
a.i.a.a. j. 1963, 231.
</BIBLIO>
<TEXT>
  paper describes results of numerical solution of the viscous
shock-layer equations for axisymmetric stagnation region, using
the viscosity-temperature law with w=0.65, pr=0.71 and
y=1.25 .  purpose is to establish applicability of the simple approximation
of w=1 (obtained earlier) to air at low reynolds
numbers and low ratios of wall temperature to stagnation
temperature .  using a reference temperature (closely equal to eckert's)
to interpret the linear results, excellent agreement is found,
in the limit of, over a wide range of reynolds numbers,
covering fully merged shock layers as well as boundary layers
with and without vorticity interaction .  agreement with recent experiments
of ferri et al is as good as to be expected from shocklayer
approximation .  paper provides valuable extension of the applicability
of the reference temperature concept .
</TEXT>
</DOC>
