<DOC>
<DOCNO>
901
</DOCNO>
<TITLE>
long slender delta wings with leading edge separation .
</TITLE>
<AUTHOR>
brown,c.e. and michael,w.h.
</AUTHOR>
<BIBLIO>
naca tn.3430.
</BIBLIO>
<TEXT>
  the slender-body approximation of linearized compressible flow is
applied to the problem of a delta wing in which flow separation occurs
at the leading edges .  the vortex sheets found in the real flow are
approximated by concentrated vortices with feeding lattices, and a
plausible adaptation of kelvin's theorem is applied to simulate the
force-free nature of the vortex sheet .
  the computations show that leading-edge separation produces an
increase in lift over that given by the jones slender-wing theory and
that the lift does not vary linearly with angle of attack .  computed
pressure distributions and span loadings are presented and the theoretical
lift results are compared with the results of simple force tests
made at a mach number of 1.9 .
</TEXT>
</DOC>
