NAVWEPS 00-807-80 
AIRPLANE PERFORMANCE 
INLET OR 
DIFFUSER COMPRESSOR 
COMBUSTION TAILPIPE 
CHAMBER TURBINE NOZZLE 
TURBOJET ENGINE CYCLE 
2 
iiT! TURBINE WORK . 
E 
2 
E Y 
it 
COMPRESSOR 
I 1 c 
VOLUME. CU. FT. 
Figure 2.6. Turbojet Engines 
108