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where the dihedral angle F is in deg. The parameter (CtplCL)A,.n is given in Fig.
3.96, KMA is giyen in Fig. 3.97, K f is given in Fig. 3.98, (Clp/CL)A is given in
Fig. 3.99, Cip] F is given in'Fig. 3.100, and KMr is given in Fig. 3.101. The value
of (Cip)}+a, given by Eq. (3.368) is per degree.
Furthermore,
Aip=_0.0005 (2)2   (3.369)
 r
                                 1.2 ~A~  ( .zw
(ACip)z" =  5-7.3  ( b) (2~/)               (3.370)
where A is the wing aspect ratio, d is the average fuselage diameter at the wing
root, b is the wing span, and zw is vertical distance between the fuselage center-
line and wing root quarter chord point, positive if the wing is below the fuselage
centerline. The value given by Eq. (3.369) is per degree2 and that given by the
Eq. (3.370) is per degree.
    For supersonic speeds, Datcoml gives the following empirical relation:
(Clp)W(B) = -0.061CN (g73) [1+A(1+A,E)] (1+ A2  )
 X(~~.)[-, +(-, )4'3]
        +r (Crp + A~p) +(AC,p)z,                                       (3.371)
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   ┃  ┃
┃  ┃        ┃    ┃  ┃~ ┃      ┃    ┃    ┃    ┃  ┃
　
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