<DOC>
<DOCNO>
1264
</DOCNO>
<TITLE>
boundary layer transition and heat transfer in shock
tubes .
</TITLE>
<AUTHOR>
hartunian,r.a., russo,a.l. and marrone,p.v.
</AUTHOR>
<BIBLIO>
j. ae. scs. 1960, 587.
</BIBLIO>
<TEXT>
  an experimental study is made of the wall boundary layer in a
shock tube operated over a wide range of shock mach numbers
and pressure levels in air, including those for which real-gas effects
exist .  transition distances are determined and correlated in
terms of the transition reynolds number based on a characteristic
length for this boundary layer .  data from independent
shock-tube studies are also included in this correlation .
  the results indicate a weak dependence of transition reynolds
number on shock strength up to moderate values of shock mach
number, followed by a larger stabilizing tendency .  comparison
of these data with transition data obtained in the same manner
in argon indicate that the increased cooling rates are largely
responsible for the stabilization .
  a dependence of transition reynolds number on the unit
reynolds number is found at the lower shock strengths .  specifically,
higher transition reynolds numbers are achieved at
larger unit reynolds numbers .
  the phenomenon of transition reversal does not appear within
the range of the experiments reported .
  laminar- and turbulent-flow heat-transfer rates to the walls
of the shock tube are determined experimentally .  the results
of the heat-transfer measurements substantiate existing theories
in both the laminar- and turbulent-flow regimes .
</TEXT>
</DOC>
