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