text: will form on each surface of the wedge and the 
  inclination of the shock wave will be a func- 
  tion of the free stream Mach number and the 
  wedge angle. As the free stream Mach number 
  increases, the shock wave angle decreases; as 
  the wedge angle increases the shock wave 
  angle increases, and, if the wedge angle is in- 
  creased to some critical amount, the shock 
  wave will detach from the leading edge of the 
  It is important to note that detach- 
  wedge. 
  ment of the shock wave will produce sub$onic 
  flow immediately after the central portion of 
  the shock wave. Figure 3.4 illustrates these 
  typical flow patterns and the effect of Mach 
  number and wedge angle. 
  
  When supersonic flow is clearly established, 
  all changes in velocity, pressure, density, flow 
  direction, etc., take place quite suddenly and 
  in relatively confined areas. The areas of flows 
  change are generally distinct and the phenom- 
  ena are referred to as “wave” 
  formations. All 
  compression waves occur suddenly and are 
  wasteful of energy. Hence, the compression 
  waves are distinguished by the sudden “shock” 
  type of behavior. All expansion waves are not 
  so sudden in their occurrence and are not waste- 
  ful of energy like the compression shock waves. 
  Various types of waves can occur in supersonic 
  flow and the nature of the wave formed depends 
  upon the airstream and the shape of the object 
  causing the flow change. Essentially, there 
  are three fundamental types of waves formed 
  in supersonic flow: (1) the oblip shock wave 
  the normal shock wave 
  (compression), (2) 
  (compression), (3) 
  the expansion wave (no 
  shock). 