text: distribution produces an inclined 
  lift with 
  drag due to lift which is in addition to the 
  wave drag at zero lift. Part (g) of figure 3.8 
  shows the wave pattern for a circular arc air- 
  foil. After the airflow traverses the oblique 
  shock wave at the leading edge, the airflow 
  undergoes a gradual but continual expansion 
  until 
  the trailing edge shock wave is en- 
  countered. Part (h) of figure 3.8 illustrates 
  the wave pattern on a conventional blunt nose 
  airfoil in supersonic flow. When the nose is 
  blunt 
  the wave must detach and become a 
  normal shock wave immediately ahead of the 
  leading edge. Of course, this wave 
  form 
  produces an area of subsonic airflow at the 
  leading edge with very high pressure and 
  density behind the detached wave. 
  
  TRANSONIC AND SUPERSONIC PLIGHT 
  
  Any object in subsonic flight which has some 
  finite thickness or is producing lift will have 
  local velocities on 
  the surface which are 
  greater than the free stream velocity. Hence, 
  compressibility effects can be expected to 
  occur at flight speeds less than the speed of 
  sound. The transonic regime of flight pro- 
  vides the opportunity for mixed subsonic and 
  supersonic flow and. accounts for 
  significant effects of compressibility. 
  
  the 
  typical patterns of supersonic flow and point 
  out these facts concerning aerodynamic surfaces 
  in two dimensional supersonic flow: 
  
  The drawings of figure 3.8 illustrate 
  
  the  first 1  (1) All 