<DOC>
<DOCNO>
1191
</DOCNO>
<TITLE>
heat transfer to a hemisphere-cylinder at low reynolds
numbers .
</TITLE>
<AUTHOR>
hickman,r.s. and giedt,w.h.
</AUTHOR>
<BIBLIO>
aiaa jnl. 1, 1963, 665.
</BIBLIO>
<TEXT>
  measurements of the local heat flux to hemispherecylinder
models in a supersonic rarefied
air stream are presented .  two different steady-state
methods were developed, and five individual
models were used .  data were obtained
throughout the mach number range of 2 to 6,
with reynolds numbers (based on conditions
behind the bow shock and model diameter) varying
from 38 to 1730 .  the stagnation point data
indicated a gradual increase from continuum
boundary layer theory at the higher reynolds
numbers to about 10 above at the lower end
of the range investigated .  pressure distribution
measurements on cooled and uncooled models
were found to agree well with modified newtonian
theory .  local recovery factor measurements
showed a small rarefaction effect at the
lowest reynolds numbers .
</TEXT>
</DOC>
