CHANGE  IN TAIL LIFT  RELATIVE WIND  FROM ANGULAR ROTATION  CHANGE IN TAIL ANGLE OF  ATTACK DUE TO PITCHING  VELOCITY  co  !!I 30  8  ;  20  MANEUVERING STICK  ::  FORCE GRADIENT  g  IO  w  I  2  3  4  5  6  7  8  LOAD FACTOR, n  (OR G)  CG POSITION  % MAC  /  LOAD FACTOR  Figure 4.15. Maneuvering Stability  269  NAVWEPS 00-801-80  STABILITY AND CONTROL 