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o 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16
f c,82 + tan2 Atl4
Fig.3.12 Subsonic winglift-curve slope.l
For subsonic speeds, the lift-curve slope of straight tapered wirigsican be deter-
mined using the data given in Fig. 3.12 or the following expression:l
au, ==
2:rr A
2+
(3.16)
where A is the aspect ratio, p = ./C~2-, k = ao/27r, and Ac/2 is the midchord
sweep. The value of ary given by Eq. (3.16) is per radian.
The sectional (two-dimensional) lift-curve slope ao is given by
ao -
[ ('.).. ] (Oo)rheory
(3.17)
Here, ao is the theoretical sectional lift curve slope given in Fig. 3.13a, and
ao/(af,)crieory is the empirical correction factor shown in Frg. 3.13b to account for
7.4
7.2
7.0
(ao) theory
6.8
(per rad)
6.6
ao
~a). u~.y
6.4
6.1
I.O
STATIC STABILITY AND CONTROL
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WING THICKNESS RArl0. t/c
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