NAVWEPS 00-801-80  AIRPLANE PERFORMANCE  TURBOJET CRUISE-CLIMB  t-  IF CL AND TAS ARE CONSTANT,  LIFT IS PROPORTIONAL TOE  IF co AND T/h ARE CONSTANT,  DRAG IS PROPORTIONAL TO a  (SPEEDS FOR MAXIMUM  FUEL  GROUNO NAUTICAL ,MlLES  FLOW  PER LB. OF FUEL)  LBS/HR  I  HEADWIND  I  /  I  IF RPM AND TAS ARE CONSTANT,  THRUST IS PROPORTIONAL TO”  (APPROXIMATE)  t-  WEIGHT DECREASES AS FUEL IS  CONSUMED  EFFECT OF WIN0 ON RANGE  -I-  VELOCITY, KNOTS  VELOCITY  VELOCITY  Figure 2.26. Range Performance  169 