0  a  FLAT PLATE WAVE PATTERN  0  c  DOUBLE WEDGE WAVE PATTERN  AT ZERO LIFT  ANGLE  ATTAC  O  e  DOUBLE WEDGE WAVE PATTERN  AT POSITIVE ANGLE OF ATTACK  NOTE: CENTER OF PRESSURE  IS AT 50% CHORD  v  b  FLAT PLATE PRESSURE DISTRIBUTION  NO NET LIFT BUT  HAVE “WAVE DRAG”  0  d REDOUBLE  WEDGE PRESSURE  DISTRIBUTION AT ZERO LIFT  DRAG DUE TO LIFT  ‘ CLEFT  L-WAVE DRAG  0  f  DOUBLEWEDGEPRESSURE  DISTRIBUTION AT POSITIVE LIFT  0  9  CIRCULAR ARC TYPE AIRFOIL  0  b  CONVENTIONAL BLUNT NOSE  AIRFOIL  Figure 3.8. Typical Supersonic Flow Patterns and Distribution of Pressure  214  NAVWEPS 00-8oT-80  HIGH SPEED.  AERODYNAMlCS 