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E
o
fH
.6 .8 1.0
b) Cone-cylinder
fr*
p
Fig.3.10 Supersonic riormal-force-curve slope.l
E
4
o:
nd)
3
C *a
(per rad)
i
Here xa will be considered positiveif the center ofgrayity is aft of the aerodynamic
center and vice versa. For conventional airplanes with wing ahead of the horizontal
tail, the wing angle of attackis approximately equal to the airplane's angle ofattack,
i.e., aw -. cy. However, for a canard airplane7he angle of attack of the wing may
be smaller than the airplane angle of attack because of the canard downwash.
In Eq. (3.14), au, is lift-curve slope of the wing in the presence of the fuselage.
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