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The permissible most forward center of gravity location is given by
                      Xcg*f = 0.4424 - (-30 -15.23215)   0~0~864
                         - 0.1167
            ~
The stick-free neutral pomt is given by
                      Chtr Cma
   (dC.)_=(,C, ,x cf -..(i-/l.)
                                                                           r _0.002)
         ---0.1424- -  ;)( 00l0864)(1-0.3)
                                                                           k -0.003)  .
                    - -0.1021
Then,
                              NL =  c8 - &Cj ),_
                                      - 0.4021
                               H,{ = - &~. )_
                                                     -. 0.1021
                                       Example 3.4
     A light aircraft has a wing loading of 1450 N/m2, wing aspect ratio of 8, and
tail aspect ratio of 4. The aerodynamic center of the wing-fuselage combination
is at 0.24 mac from the wing leading edge. The static margin is -0.05. Using the
following data, determine the tab deflection to trim the stick force at a speed of
160 km/h in level fiight at sea level. What is the stick force gradient at this speed?
     a,,  -.  a, = O.l/deg, croL.u, = /t - /w = 0, 8e = -2 deg,  Vi  = 0.6, e = 0.5a,  r7t =
0.9, q". f  = O.ICL, r = 0.5, Se - 1.85 m2,ce = 0.608 m, Chot--0.003ldeg, Ch&= '
- 0.006]deg, Ch.o = 0, Ch8, = -0.003/deg, and Gi :5.0 rad/m.
  Solution.  This aircraft is statically unstable because it has negative static
margin (Hn - -0.05). We have
                                                 1
                          8uim = --,,,.,(-. .  +K2)
where
                  K"=-K, .C ~(:g )_
                                     K' = ;:pK]
246            PERFORMANCE, STABILl-fY, DYNAMICS, AND CONTROL
and
                         K2 = Cho + Cha(aw.oL - iw + /,) + CM.e8eo   .
　
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