text: where 
  
  condition (1) applies to some known condi- 
  tion of weight, 
  fuel flow, and specific 
  range at some original basic altitude 
  during cruise climb. 
  
  con&&r (2) applies to some new values of 
  weight, fuel flow, and specific range at 
  some different altitude along a partic- 
  ular cruise path. 
  
  and 
  
  V= velocity, knots 
  M = Mach number 
  W= gross weight, lbs. 
  flow, lbs./hr. 
  FF=fuel 
  JR= specific range, nmi./lb. 
  e=altitude density ratio 
  
  For example, if the cruise fuel weight is 50 per- 
  cent of the gross weight, the climbing cruise 
  flight path will provide a range 18.2 percent 
  greater than cruise at constant ,altitude. This 
  comparison does not include consideration of 
  any variation of specific fuel consumption dur- 
  ing cruise or the effects of compressibility in 
  defining the optimum aerodynamic conditions 
  for cruising flight. However, the comparison 
  is generally applicable for aircraft which have 
  subsonic cruise. 
  no change in Mach number or ‘TAS 
  a 5 percent decrease in EAS 
  a 10 percent decrease in C, i.e., higher 