Analysis of factors affecting net lift increment attainable with trailing-edge split flaps on tailless airplanes Page: 4 of 41
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NACA ARR No. L118
fixed angle of attack by means of flaps creating zero
pitching moments about the wing aerodynamic center. Addi-
tional calculations were made to determine the losses in
lift resulting from the elevator deflectibns required to
trim stability moments. A brief study-was made of
available empirical data concerning the effect of sweep-
back and flaps upon the maximum lift probable in trimmed
flight.
The lift increments of different flap arrangements
were determined by the method of reference 1 with a
simple chord correction factor being applied. The
pitching moments were computed from a consideration of
the incremental lift due to the action of the flaps at
each spanwise section and the center of pressure of this
incremental lift. This procedure is somewhat similar in
basic principles to the method of reference 2. The
accuracy of the present method was determined by calcu-
lating by means of this method the lift and moment incre-
ments of flaps on 10 different finite wing-flap combina-
tions for which wind-tunnel data were available.
SYMBOLS
a angle of attack, degrees
CL lift coefficient Lift
qS /
CLmax maximum lift coefficient
01 section lift coefficient Section lift)
qc
maximum lift coefficient in trimmed flight
ACL increment of lift coefficient
CM pitching-moment coefficient Pitchingmoment
cm section pitching-moment coefficient
(Section pitching moment1
qc2I
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Maggin, Bernard. Analysis of factors affecting net lift increment attainable with trailing-edge split flaps on tailless airplanes, report, September 1944; (https://digital.library.unt.edu/ark:/67531/metadc61281/m1/4/: accessed April 23, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.