<DOC>
<DOCNO>
226
</DOCNO>
<TITLE>
aerofoil theory of a flat delta wing at supersonic
speeds .
</TITLE>
<AUTHOR>
robinson,a.
</AUTHOR>
<BIBLIO>
rae r.aero.2151, 1946.
</BIBLIO>
<TEXT>
  lift, drag, and pressure distribution of a triangular
flat plate moving at a small incidence at supersonic
speeds are given for arbitrary mach number and aspect ratio .
the values obtained for lift and drag are compared with
the corresponding values obtained by strip theory .  the
possibility of further applications of the analysis leading up
to the above results is indicated .
</TEXT>
</DOC>
