text: where 
  
  T= thrust available, lbs. 
  D= drag, lbs. 
  W= weight, lbs. 
  path 
  v=flight  inclination or angle ,of 
  
  climb, degrees (“gamma”) 
  
  This basic relationship neglects some of the 
  factors which may be of importance for air- 
  planes of very high climb performance. For 
  example, a more detailed consideration would 
  account for the inclination of thrust from the 
  flight path, lift not equal to weight, subse- 
  quent change of induced drag, etc. However, 
  this basic relationship will define the principal 
  factors affecting climb performance. With 
  this relationship established by the condition 
  relationship 
  of equilibrium, 
  exists to express the trigonometric sine of the 
  climb angle, y: 
  
  the  following 
  
  The thrust curves for the representative jet 
  aircraft show the typ~ical turbojet thrust which 
  the 
  is very nearly constant ~with speed. If 
  thrust available is essentially constant with 
  speed, the maximum excess thrust and angle 
  of climb will occur where the thrust required 
  
  T-D 
  W 