Figure 6.15. Planform Views of an Early F-16A and an F-16C
The stability analysis begins by estimating the location of the aerodynamic center of the wing/strake/fuselage combination, which will be the same for both aircraft. For the F-16 wing alone:
= ctip / croot = 3.5 ft /16.5 ft = 0.212
 = 11.4 ft
 = 5.875 ft
xac = yM.A.C. tan LE + 0.25 M.A.C. (subsonic)
= (5.875 ft) tan 40o + 0.25 ( 11.4 ft) = 7.8 ft
x ac = yM.A.C. tan LE + 0.50 M.A.C. (supersonic)
= (5.875 ft) tan 40o + 0.50 ( 11.4 ft) = 10.6 ft
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