text: In order to obtain a high critical Mach 
  lift 
  
  number from an airfoil at some low 
  coefficient the section must have: 
  
  thickness ratio. The point of 
  maximum thickness should be aft to smooth 
  the pressure distribution. 
  
  (u) Low 
  
  (6) Low camber. The mean camber line 
  the 
  
  should be shaped to help minimize 
  local velocity peaks. 
  
  lift 
  In addition, 
  coefficient the lower the critical Mach number 
  and more camber is required of the airfoil. 
  If supersonic flight 
  the thick- 
  ness ratio and leading edge radius must be 
  small to decrease wave drag. 
  
  the higher  the  required 
  
  is a possibility 