NAVWEPS 00-BOT-80 
AIRPLANE PERFORMANCE 
COMPRESSOR STALL 
COMPRESSOR 
COMBUSTION EXHAUST 
CHAMBER T”RB,NE NOZZLE 
PRESSURE RISE 
LIMITED BY 
STATIC 
PRESSURE 
CHANGE 
INLET 
INCREASED 
BLADE ANGLE 
ROTATING 
COMPRESSOR 
,STEADY STATE 
AXIAL FLOW VEL 
/ VELOCITY COMPONENT 
DUE TO ROTATION 
EFFECT OF INLET TEMPERATURE 
-REDUCED AXIAL 
FLOW VELOCITY 
TEMPERATURE EXHAUST 
CHANGE TEMPERATURE RISE 
THROUGH COMBUSTION 
-- CHAMBER 
INLET 
.OCITY 
COMPRESSOR COMBUSTION TURBINE EXHAUST 
CHAMBER NOZZLE 
Figure 2.13. Effect of Compressor Stall ond Inlet Temperature on Engine Operation 
126