text: boundary layer along the fuselage surface. At 
  supersonic flight speeds, the diffuser must slow 
  the least waste of 
  the air to subsonic with 
  energy in the inlet air and accomplish the 
  process with a minimum of aerodynamic drag. 
  the inlet must be efIicient and 
  In addition, 
  stable in operation throughout 
  the range of 
  angles of attack and Mach numbers of which 
  the airplane is capable. 
  
  The partial expansion of the gases through 
  the turbine will provide the power to operate 
  the engine. As. the gases are discharged from 
  the turbine at point F, expansion will continue 
  through the tailpipe nozzle. until atmospheric 
  pressure is achieved in the exhaust. Thus, 
  continued expansion in the jet nozzle will 
  re- 
  duce the pressure and increase the volume of 
  the unit weight of air to point G on the pressure 
  the final jet 
  volume diagram. As a result, 
  velocity is greater than the inlet velocity and 
  the momentum change necessary for the .de- 
  velopment of thrust ha~s’been created. The 
  area YFGA represents the work remaining to 
  provide the expansion to jet velocity after the 
  turbine has extracted the work 
  requited to 
  operate the compressor. 