<DOC>
<DOCNO>
340
</DOCNO>
<TITLE>
analysis of effects of diffusion of a foreign gas into
the laminar boundary layer of a supersonic flow of
air in a tube .
</TITLE>
<AUTHOR>
radbill,j.r. and kaye,j.
</AUTHOR>
<BIBLIO>
j.ae.scs. 26, 1959.
</BIBLIO>
<TEXT>
  adiabatic wall temperatures and recovery factors are calculated
for pipe flows with an entrance mach number of 5 and with uniform
injection of helium .  predicted values of the recovery factor increase
slowly with increasing injection rate and with increasing
distance from the tube entrance .
</TEXT>
</DOC>
