<DOC>
<DOCNO>
666
</DOCNO>
<TITLE>
blunt body heat transfer at hypersonic speed and low reynolds numbers .
</TITLE>
<AUTHOR>
ferri, a. zakkay, v. and ting, l.
</AUTHOR>
<BIBLIO>
j. aero. sc. v. 28. p. 862. 1961 .
</BIBLIO>
<TEXT>
an analytical method for the determination of effect of shock curvature
on heat transfer in the region of the nose has been developed . it is
shown that for practical body shape the viscous terms in the navierstokes
equations are not important in the region of the flow far from
the wall, and the displacement thickness can be neglected . then the
flow can be approximately represented by an inviscid-flow solution
having as boundary conditions the body shape, which is not affected by
the reynolds number, and by a boundary-layer type of flow near the
wall, having appropriate boundary conditions . this approach permits us
to determine the heat transfer in the region of the nose even at very
low reynolds numbers .
experimental results are presented . the experimental results agree
with the values given by the analysis .
</TEXT>
</DOC>
