<DOC>
<DOCNO>
780
</DOCNO>
<TITLE>
the transonic characteristics of 38 cambered rectangular
wings of varying aspect ratio and thickness as determined
by transonic-bump technique .
</TITLE>
<AUTHOR>
nelson,w.h. and krumm,w.j.
</AUTHOR>
<BIBLIO>
naca tn.3502, 1955.
</BIBLIO>
<TEXT>
  an investigation to determine
the effects of camber on the aerodynamic
characteristics of a series
of rectangular wings having various
aspect ratios and thickness-to-chord
ratios was conducted in the ames
the transonic-bump method .
the mach number range of the
investigation was from 0.6 to 1.12, with
a corresponding reynolds number
range of 1.7 to 2.2 million .  the lift,
drag, and pitching-moment data
are presented for wings having aspect
ratios of 4, 3, 2, 1.5, and 1,
and naca 63a2xx and 63a4xx sections with
thickness-to-chord ratios of
</TEXT>
</DOC>
