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National Advisory Committee for Aeronautics, Technical Notes - The Effect of Split Trailing Edge Wing Flaps on Aerodynamic Characteristics of a Parasol Monoplane

This paper presents the results of tests conducted in
the N.A.C.A. full—scale wind tunnel on a Fairchild F—22 e
airplane equipped with a special wing having split trailing—
edge flaps. The flaps extended over the outer 90 percent "1
of the wing span. and were of the fixed—hinge'tipe having a ~
width equal to 20 percent of the wing chord.

The results show that with a flap setting of 53° the
maximum lift of the wing was increased 42 percent,_and_that
the flaps increased the range of available gliding angles'
from 2.70 to 7.00. Deflection of the split flaps did not
increase the stalling angle or seriously_affect the longi—
tudinal balance of the airplane. With flaps dOWn the land—
ing speed of the airplane is decreased, but the calculated
climb and level—flight performance is inferior to that_with
the normal wing. Calculations indicate that the—taieloff
distance required to clear an obstacle 100 feet highfis not
affected by flap settingSfrom O°to 20° but is greatly in-
creased by larger flap angles.

Considerable attention has recently been directed to
the use of split trailing—edge wing flaps as a device for
reducing the landing run and increasing the gliding angle
of airplanes. As a part of its general research prograg»
dealing with high lift devices, the National Advisory _'”
Committee for Aeronautics has conducted comprehensive model
tests in the 7 by 10 foot wind tunnel on split trailing—
edge flaps (reference 1), and is now conducting full—scale
investigations of this device on a Fairchild—BB parasol
monoplane.

This paper presents the results of tests conducted
in the N.A.C.A. full—scale wind tunnel to determine the
aerodynamic characteristics of -the Fairchild F— 22 airplane
when equipped with a special wing having split trailing—
edge flape ext_ending over 90 percent_ of_ the syan.__ _The
i‘laps We.re hinged at their forward edge and had a width
equal to 20 percent of the wing chord. Absolute coeffi—
cients o£ lift, drag, and p-itching.