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 