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This increase in elevator defiection is usually expressed by the parameter (d8e/dn),
which is the elevator deflection per unit increase in load factor above unity.
From Eq. (3.101), we have
                                                                                  d8e                         ( dC, )m
                  ~ig ), =-  .                 (3.199)
With
      xcg - Nm
  Cm8
(3.200)
 ddC~), = dd8 ddr;                    (3.201)
and
                           dn .  1
           (3.202)
 .                            d~L = CL
we obtain
                                                      d8c         . CL(Xcg - Nm)
                               -            (3.203)
                              d7z -- --    CmS
Usually, for a stable airplane, Xc8  <  Nm and Cm8  < 0 so that we have d8e]dn  < 0-
Thus, to pull higher load factors during the maneuver, more up elevator deflection
is required compared to that in level fiight at the same altitude and forward speed.
This incremental elevator deflection.can be expressed as
                                    A8, = _C (xc8 - Nm)An
                          -        ' (3.204)
            Cm8
   Stick-free maneuver point.   Suppose that the e     or is left free to float
during a pull-up maneuver. Then, the horizontal ta,'~_;'e.   at'a'k is given by
                  ctt - (CtW -/LU+/t -6+A :.,) (1-     -,,.,)          (3.205)
so that
     dar
   - =[.1.(1-~)+-,,,1(,-,-....) (3.206)
               dCL =
Then,
 G~ )..=-ti,+(;g ),--.. (i-:)+2v-,](i-,cC,,.,)
           (3.207)
                                                                      ~
       N;" =  ac*w - GC/  )f + -V  7  [(1 - i) + 2p~,] (1 -,CC,,.,)
                             .  (3.208)
　
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