text: An airplane may be designed to be “stall- 
  proof” simply by reducing the effectiveness of 
  the elevators. 
  If the elevators are not power- 
  ful enough to hold the airplane to high angles 
  of attack, the airplane cannot be stalled in any 
  condition of flight. Such a requirement for a 
  tactical military airplane would seriously re- 
  duce performance. High lift coefficients near 
  the maximum are required for high maneuver- 
  ability and low 
  landing and takeoff speeds. 
  Hence, the Naval Aviator must appreciate the 
  effect of the many variables affecting the stall 
  angle of 
  speed and regard “attitude 
  attack 
  indicators, and stall warning devices 
  as techniques which allow more precise control 
  of the airplane at high lift conditions. 
  
  flying,” 
  
  One factor common to maximum lift condi- 
  tion is the angle of attack and pressure distri- 
  bution. The maximum lift coefficient of a 
  particular wing configuration 
  is obtained at 
  one angle of attack and one pressure distribu- 
  tion. Weight, bank angle, load factor, density 
  altitude, and airspeed have no direct effect on 
  the stall angle of attack. This fact is sufficient 
  justification for the use of angle of attack indi- 
  cators and stall warning devices which sense 
  pressure distribution on the wing. During 
  flight maneuvers, landing approach, takeoff, 
  turns, etc. the airplani will stall if the critical 
  angle of attack is cxcccdcd. The airspeed ar 
  which stall occurs will be determined by 
  weight, load factor, and altitude but the stall 