text: stabilizing so that the complete configuration 
  will exhibit positive static stability at the 
  In addition, the tail 
  anticipated c.g. locations. 
  and wing incidence must be set to provide a 
  trim lift coefficient near the design condition. 
  When the configuration of the airplane is 
  fixed, a variation of c.g. position can cause 
  large changes in the static stability. 
  In the 
  conventional airplane configuration, the large 
  changes in stability with c.g. variation are 
  primarily due to the large changes in the wing 
  contribution. 
  If the incidence of all surfaces 
  remains fixed, the effect of c.g. position on 
  is typified by the 
  static longitudinal stability 
  second chart of figure 4.10. As the cg. 
  is 
  gradually moved aft, the airplane static sta- 
  bility’ decreases, then becomes neutral 
  then 
  unstable., The c.g. position which produces 
  zero ,slope and neutral static stability 
  is re- 
  ferred to asp the ~“neutral point.” 
  The neutral 
  point may be imagined as the effective aerody- 
  namic center of the entire airplane configura- 
  ration, i.e., with 
  the c.g. at this position, all 
  changes in net lift effectively occur at this 
  point and no change in pitching moment 
  results. The neutral point defines the most 
  aft c.g. position without static instability. 