<DOC>
<DOCNO>
1280
</DOCNO>
<TITLE>
wings with minimum drag due to lift in supersonic flow .
</TITLE>
<AUTHOR>
ginzel,i. and multhopp,h.
</AUTHOR>
<BIBLIO>
j. ae. scs. 1960, 13.
</BIBLIO>
<TEXT>
  it has been shown by r. t. jones that, in order to produce
minimum drag, the given lift must be distributed over the wing
surface in such a way that the sum of the downwash induced by
this distribution and the downwash induced in reversed flow is
constant over the wing surface .  this combined downwash can be
expressed by an integral which contains the load as a function
of the spanwise and chordwise coordinate .  the problem of
finding the appropriate load distribution is thus reduced to the
problem of finding the solution of a rather cumbersome integral
equation .
  the severe spanwise singularity of the kernel function is
handled most easily, as in corresponding subsonic problems, by an
approximate integration over interpolation polynomials .  the
chordwise load distribution is represented by a limited series
development in legendre polynomials .  the sigularity of the
kernel function along the mach lines through any pivotal point
can be avoided by a similar legendre development of the combined
induced downwash which is constant .  the integral equation
is thus converted into a system of linear equations for the
unknown coefficients of the legendre functions of the load distribution
at a limited number of spanwise stations .
  practical calculations are carried out on an electronic computer
.  the solutions yield the optimum load distribution and the
local incidence (twist, camber, etc.) necessary to realize this
distribution .  for many wing plan forms, considerable gains
over a plane wing appear possible .
</TEXT>
</DOC>
