<DOC>
<DOCNO>
293
</DOCNO>
<TITLE>
recent studies on the effect of cooling on boundary
layer transition at mach 4.
</TITLE>
<AUTHOR>
wisniewski,r.j. and jack,j.r.
</AUTHOR>
<BIBLIO>
j. ae. scs. 28, 1961.
</BIBLIO>
<TEXT>
the advent of high-speed flight has necessitated the study of
boundary-layer transition on highly cooled bodies .  investigations
such as those of references 1-4 have concentrated
on this problem and have indicated, contrary to the trends
predicted by small-disturbance theory, that premature transition
can be found with cooling .  this phenomenon, commonly called
detail in references 2-5 .
  the purpose of this note is to report some recent transition
data obtained on a cooled cone in a mach 4 wind tunnel .  the
model, a sharp-tip cone (included angle 13.5), was cooled by
liquid nitrogen to a temperature of -340 f .  the cooling
method and the data analysis are similar to that described in
reference 3 .
</TEXT>
</DOC>
