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National Advisory Committee for Aeronautics, Report - Calculation of the Aerodynamic Characteristics of Tapered Wings with Partial Span Flaps

Factors derived from wing theory are presented. By
means of these factors, the angle of zero lift, the lift-curse
slope, the pitching moment, the aerodynamic-center posi—
tion, and the induced drag of tapered wings with partial-
span flaps may be calculated. The factors are given for
wings of aspect ratios 6' and 10, of taper ratios from 0.25
to 1.00, and with flaps of various lengths.

An example is presented of the method of application of
the factors. Fair agreement with experimental results is
shown for two wings of diferent taper ratio having plain
flaps of various spans.

Because of the widespread use of tapered wings
equipped with partial-span flaps, it is desirable to have
means for computing their aerodynamic characteristics.
Previous reports (references 1, 2, and 3) have presented
theoretical factors for use in computing the aerodynamic
characteristics of wings with linear and with arbitrary
twist and for use in finding the load distribution of
wings with partial-span flaps.

This report presents factors, based on airfoil theory,
for use in calculating the induced drag, the angle of
zero lift, the pitching moment, and the aerodynamic
center of tapered Wings with partial-span flaps of con-
stant flap—chord ratio. The factors, when used with
adequate section data, should apply to various types of
flap and various amounts of flap deflection.

The particular wing chord distributions for which the
theoretical computations were specifically made are
given in figure 1 where the wing quarter-chord line is
shown as straight. Two aspect ratios (A=6 and 10)
and four taper ratios 0:1.00, 0.75, 0.50, and 0.25)
were used. A list of the symbols used herein is given
in appendix A. Inasmuch as the various characteris-
tics for elliptical wings with partial-span flaps could be
obtained relatively easily, they were sometimes com-
puted in order to aid in determining the shape of the
various computed curves for the tapered wings.