text: and high power, the dynamic pressure in the 
  shaded area can be much greater than the free 
  stream and this causes considerably greater 
  lift 
  than at zero thrust. At high power con- 
  ditions the induced flow also causes an effect 
  similar to boundary layer control and increases 
  the maximum lift angle of attack. The typical 
  four-engine propeller driven airplane may have 
  60 to 80 percent of the wing area affected by 
  the induced flow and power effects on stall 
  speeds may be considerable. Also, the lift of 
  the airplane at a given angle of attack and air- 
  speed will be greatly affected. Suppose the 
  airplane shown is in the process of landing 
  flare from a power-on approach. 
  If there is 
  a sharp, sudden reduction of power, the air- 
  plane may drop suddenly because of the reduced 
  lift. 
  
  net lift produced by the airfoil 
  is difference 
  between the lifts on the upper and lower sur- 
  faces. The point along the chord where the 
  is effectively concentrated is 
  distributed 
  termed the “center of pressure, c.p.“ 
  The 
  center of pressure is essentially the “center of 
  gravity” 
  lift pressure and 
  the location of the c.p. is a function of camber 
  and section lift coe&cient 
  
  lift 