text: The maximum range condition is obtained 
  at maximum lift-drag ratio and it is important 
  for a given airplane 
  to note that (L/D),, 
  configuration occurs at a particular angle of 
  attack and li5t coefficient and is unaffected by 
  weight or altitude 
  compressibility 
  Since approximately 50 percent of 
  limits). 
  the total dra.g a’t (L/D)*
  is induced drag, the 
  propeller powered airplane which is designed 
  specifically i3r IJong range will have a strong 
  preference for rbe thigh aspect rario planform. 
  The effect ,df tihe variation of airplane gross 
  weight is illustrated by the second graph of 
  figure 2.24. ‘The flight condition of (L/D),., 
  is achieved a’t,one-particular value of lift coefIi- 
  cient 
  for a given airplane configuration. 
  Hence, a variation of gross weight will alter 
  the values of airspeed, power required, and spe- 
  cific range obtained at (L/D)m.r. 
  If a given 
  configuration ‘of airplane is operated at con- 
  lift 
  stant altitude and the 
  coefficient for 
  relationships will 
  following 
  the 
  WDL 
  awb 