text: The operation of the compressor can be af- 
  fected greatly by the uniformity of flow at the 
  compressor face. When large variations 
  in 
  flow velocity and direction exist at the face of 
  the axial compressor, the efficiency and stall- 
  surge limits are lowered. Thus, the flight 
  conditions which involve high angle of attack 
  and high sideslip can cause deterioration of 
  inlet performance. 
  
  The compreJ.ror s&on is one of the most im- 
  portant components of the turbojet engine. 
  The compressor must furnish the combustion 
  chamber with large quantities of high pressure 
  air in a most efficient manner. Since the com- 
  pressor of a jet engine has no direct cooling, 
  the compression process takes place with a 
  minimum of heat Ioss of the compressed air. 
  Any friction 
  loss or inefficiency of the com- 
  pression process is manifested as an undesirable 
  additional increase in the temperature of the 
  compressor discharge air. Hence, compressor 
  efficiency will determine the compressor power 
  necessary to create the pressure rise of a given 
  airflow and will affect the temperature change 
  which can take place in 
  the combustion 
  chamber. 
  
  The compressor section of a jet engine may 
  be an axial flow or centrifugal flow compressor. 
  The centrifugal flow compressor has great util- 
  ity, simplicity, and flexibility of operation. 
  The operation of the centrifugal compressor 
  requires relatively 
  low inlet velocities and a 
  plenum chamber or expansion space must be 
  provided for the inlet. The impeller rotating 
  at high speed receives the inlet air and pto- 
  vides high acceleration by virtue of centrifugal 
  force. As a result, the air leaves the impeller 