text: For the airplane shown, the positive limit 
  load factor is 7.5 and the, positive ultimate 
  load factor is Il.25 
  For negative 
  load 
  lift 
  flight conditions the negative’limit 
  factor is 3.0 and the negative ultimate 
  load 
  The limrt airspeed is 
  factor is 4.5 (3.0x1.5). 
  stated as 575 knots while the wing level stall 
  speed is apparently 100 knots. 
  
  (7.5x1.5)- 
  
  Figure 5.4 provides supplementary informa- 
  tion to illustrate 
  the significance of the V-n 
  diagram of figure 5.3. The lines of maximum 
  lift capa’bility are the first points of importance 
  on the’ V-n diagram. The subject aircraft is 
  capable bf developing no more than one posi- 
  tive “g” at 100 knots, the wing level stall speed 
  of the airplane. Since the maximum load 
  the square of the aitspeed, 
  faztor varies with 