<DOC>
<DOCNO>
783
</DOCNO>
<TITLE>
a method for calculating the subsonic steady-state loading on an airplane
with a wing of arbitrary planform and stiffness .
</TITLE>
<AUTHOR>
gray, w.l.
</AUTHOR>
<BIBLIO>
naca tn 3030, 1953 .
</BIBLIO>
<TEXT>
a method for computing the steady-state span load distribution on an
elastic airplane wing for specified airplane weights and load factors is
 given . the method is based on a modification of the weissinger lmethod
and applies at subcritical mach numbers . it includes the effects
 of external stores and fuselage on the spanwise loading . modifications
are outlined for treating tail-boom and tailless airplane configurations
and for calculating the divergence dynamic pressure of a
swept wing with a large external store . a method is also outlined for
reducing wind-tunnel data to obtain effective aerodynamic coefficients
which are free of model flexibility effects . the effects of mach number
 can readily be evaluated from the aerodynamic coefficients thus obtained
.
</TEXT>
</DOC>
