<DOC>
<DOCNO>
1186
</DOCNO>
<TITLE>
lift of slender delta wings according to newtonian
theory .
</TITLE>
<AUTHOR>
messiter,a.f.
</AUTHOR>
<BIBLIO>
aiaa jnl. 1963,795
</BIBLIO>
<TEXT>
  an approximate system of equations is derived to
describe the inviscid flow past a flat slender
wing at angle of attack, in the limit and .
the aspect ratio is required to
approach zero at the same rate as the mach angle in
the flow behind the shock wave .  only a
single parameter appears in the resulting equations,
and a similarity law therefore can be
written expressing a correction to the newtonian
normal-force coefficient .  for the delta wing,
a correlation of experimental data according to the
similarity law is shown, and the first terms
of the solution are derived under the assumption
that the similarity parameter is small (vertex
angle much smaller than mach angle) .
</TEXT>
</DOC>
