<DOC>
<DOCNO>
391
</DOCNO>
<TITLE>
flutter of rectangular simply supported panels at high
supersonic speeds .
</TITLE>
<AUTHOR>
hedgepeth,j.m.
</AUTHOR>
<BIBLIO>
j. ae. scs. 24, 1957.
</BIBLIO>
<TEXT>
  the problem of panel flutter of rectangular simply supported
plates subjected to supersonic flow over one surface is treated
theoretically .  the assumption is made, and subsequently verified,
that the /static/ approximation to the aerodynamic flutter
forces yields flutter boundaries with satisfactory accuracy for
mach numbers greater than about 2 .  two panel flutter analyses
are performed using this static approximation in conjunction with
thin-plate theory--one employs aerodynamic strip theory, the
other aerodynamic surface theory .  the influence of mach
number, dynamic pressure, panel aspect ratio, and midplane
stress on the panel thickness required to prevent flutter is determined
for extensive ranges of these parameters .
</TEXT>
</DOC>
