text: supersonic drag due to lift is a function of the 
  section and angle of attack while the subsonic 
  induced drag is a function of lift coefficient 
  and aspect ratio. This comparison makes it 
  obvious that supersonic flight does not demand 
  the use of high aspect ratio planforms typical 
  fact, low aspect 
  of low speed aircraft. 
  ratios and high taper are favorable from the 
  standpoint of structural considerations if very 
  thin sections are used to minimize wave drag. 
  If sweepback is applied to the supersonic 
  wing, the pressure distribution will be affected 
  by the location of the Mach cone with respect 
  to the leading edge. Figure 3.19 illustrates the 
  pressure distribution 
  for the delta wing plan- 
  form in supersonic flight with the leading edge 
  behind or ahead of the Mach cone. When the 
  leading edge is behind the Mach cone the com- 
  ponents of velocity perpendicular to the leading 
  edge are still subsonic even though the free 
  is supersonic and the resulting 
  stream flow 
  pressure distribution will greatly resemble the 
  subsonic pressure distribution 
  for such a plan- 
  form. Tailoring 
  the leading edge shape and 
  camber can minimize the components of the 
  high leading edge suction pressure which are 
  inclined in the drag direction and the drag due 
  If the leading edge 
  to lift can be reduced. 
  is ahead of the h4ach cone, the flow over this 
  area will correspond to the two-dimensional 
  supersonic flow and produce constant pressure 
  for that portion of the surface between the 
  leading edge and the Mach cone. 