<DOC>
<DOCNO>
1106
</DOCNO>
<TITLE>
free-flight observation of a separated turbulent flow
including heat transfer up to mach 8. 5.
</TITLE>
<AUTHOR>
mcconnell,d.g.
</AUTHOR>
<BIBLIO>
nasa tn.d278, 1961.
</BIBLIO>
<TEXT>
  a turbulent boundary layer separated
by a forward-facing step was
observed on the cylindrical portion
of a hemisphere-cone-cylinder test
vehicle .  tip blunting, producing a
shear flow, was found to induce
higher pressures on the cylindrical
portion than were predicted from ballistic
tunnel data of unblunted projectiles .
an approximate method for
predicting this blunt-body pressure
distribution was hypothesized .  these
findings, along with the hypothesis,
were substantiated by a wind tunnel
test of a similar body .  the peak pressure
ratios of the separation were
smaller in magnitude than flat plate
theory predicted because of the
effect of the shear flow .  the decrement
in heating of the separated
flow, relative to the corresponding
attached flow, was found to compare
well with the expected results .
</TEXT>
</DOC>
