<DOC>
<DOCNO>
1394
</DOCNO>
<TITLE>
stagnation point heat transfer measurements in hypersonic
low density flow .
</TITLE>
<AUTHOR>
neice,s.e., rutkowski,r.w. and chann,k.k.
</AUTHOR>
<BIBLIO>
j. ae. scs.27, 1960, 387.
</BIBLIO>
<TEXT>
in hypersonic, low reynolds number flow around a blunt body,
the boundary-layer thickness approaches the shock-layer
thickness (shock standoff distance) within the region of continuum
flow .  in this instance, the customary boundary-layer
approximations no longer apply .  hoshizaki and probstein
have obtained solutions to the incompressible navier-stokes
equations in the stagnation region of a blunt body in this hypersonic
low reynolds number flow .  the results indicate that heattransfer
rates are substantially higher than those predicted by incompressible
boundary-layer theory .  probstein indicated that
the actual heat-transfer rates would be correspondingly higher
than the predictions of fay and riddell .  these findings are of
particular importance in the atmospheric entry phase of recoverable
satellites .
</TEXT>
</DOC>
