<DOC>
<DOCNO>
227
</DOCNO>
<TITLE>
a technique for improving the predictions of linearised
theory on the drag of straight edge wings .
</TITLE>
<AUTHOR>
randall,d.g.
</AUTHOR>
<BIBLIO>
arc cp394, 1957.
</BIBLIO>
<TEXT>
  the curve of drag against mach number for straight-edged wings,
calculated by using the linearised theory of supersonic flow, displays
discontinuities in slope at the various mach numbers for which the edges
are sonic .  these features, which are not observed in practice, are due
to the fact that linearised theory predicts an infinite pressure along
a subsonic or sonic edge .  it is shown that if the linearised equation
of supersonic flow is used to determine the flow over straight-edged
wings, but the linearised boundary condition is replaced by the full
placed by plausible values .  on this basis a simple method is derived
for improving the linearised predictions of the drag of straight-edged
wings which exhibits satisfactory agreement with experimental results .
  while the technique is not directly applicable to ridge lines, an
artifice renders them amenable to similar treatment .
</TEXT>
</DOC>
