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where CN iS the normal force coefficient, CNcr iS the wing normal-force-curve
slope (per radian) and can be evaluated using the methods given in Section 3.3, A,
is the wing taper ratio, ALE is the wing leading-edge sweep in radians, A is the
wing aspect ratio, and F is the wing dihedral in degrees. The value of (Clp)WcB)
given by Eq. (3.371) is per degree. Furthennore,
CFp = (5 23 ) (:~;:) C,P (3.372)
where Clp is'the roll damping parameter assumed to be known. We will learn
more about roll damping when we discuss dynamic stability in Chapter 5. The
parameters ACtp/ r and (ACip)z. are given by Eqs. (3.369) and (3.370).
STATIC STABILITY AND CONTROL
SUBSONIC SPEEDS
Ac/2 (deg)
-20' 0 20 40 60 80
.002
0
( -)-.,2.002
(per deg) -.004
' .006
-*008
-.010
(~-)A.2
(per deg)
G~,,
(per deg)
┏━┳━━━━┳━━┳━┳━┳━━━┳━━┳━━┳━━┳━┓
┃~ ┃(a) 7. ┃- ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃
┃ ┃~ ┃ I ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃
┣━╋━━━━╋━━╋━╋━╋━━━╋━━╋━━╋━━╋━┫
┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃
┣━╋━━━━╋━━╋━╋━╋━━━╋━━╋━━╋━━╋━┫
┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃A ┃ ┃
┃ ┃ ┃ ┃ ┃ ┃ ┃~ ┃\ ┃ I ┃ ┃
┣━╋━━━━╋━━╋━╋━╋━━━╋━━╋━━╋━━╋━┫
┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃2 ┃ ┃
┣━╋━━━━╋━━╋━╋━╋━━━╋━━╋━━╋━━╋━┫
┃ ┃ ┃~ ┃X ┃~ ┃) - ┃"- ┃~~ ┃4 ┃ ┃
┃ ┃ ┃ ┃ ┃~ ┃ ┃ ┃ ┃ ┃ ┃
┣━╋━━━━╋━━╋━╋━╋━━━╋━━╋━━╋━━╋━┫
┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃6 ┃ ┃
┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃8 ┃ ┃
┗━┻━━━━┻━━┻━┻━┻━━━┻━━┻━━┻━━┻━┛
Ac/2 (deg)
┏━┳━━━━━━━━━┳━━━┳━┳━┳━┳━┳━━┳━┳━┓
┃~ ┃(b) ┃k= .5 ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃
┃ ┃ ! ┃1 ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃
┣━╋━━━━━━━━━╋━━━╋━╋━╋━╋━╋━━╋━╋━┫
┃ ┃ ┃~ ┃X ┃~ ┃ ┃ ┃ ┃ ┃ ┃
┣━╋━━━━━━━━━╋━━━╋━╋━╋━╋━╋━━╋━╋━┫
┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃ ┃A ┃ ┃
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PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL2(79)
