text: Thus, a sea level airspeed (or EAS) of 100 
  knots would provide the dynamic pressure 
  necessary at maximum lift 
  to produce 14,250 
  Ibs. of lift. 
  If the airplane were operated at a 
  higher weight, a higher dynamic pressure 
  would be required to furnish the greater lift 
  and a higher stall speed would result. 
  If the 
  airplane were placed in a steep turn, the greater 
  increase the 
  lift 
  stall speed. If the airplane were flown at a 
  higher density altitude the TAX at stall would 
  increase. However, one factor common to 
  each of these conditions is that the angle of 
  attack at C,,,, is the same. It is important 
  to 
  realize that stall warning devices must sense 
  angle of attack (a) or pressure distribution 
  (related to CL). 
  
  required in the turn would 
  
  Another important fact related by the basic 
  lift equation and lift curve is variation of angle 
  of attack and lift coefficient with airspeed. 
  Suppose that the example airplane is flown in 
  steady, wing 1eveJ flight at various airspeeds 
  It is obvious 
  with 
  that an increase in airspeed above the stall 
  speed will require a corresponding decrease in 
  lift coeflicient and angle of attack to maintain 
  The exact 
  steady, lift-equal-weight 
  relationship of lift coefficient and airspeed is 
  evolved from the basic lift equation assuming 
  constant lift (equal to weight) and equivaIent 
  airspeeds. 