NAVWEPS 00-BOT-80  HIGH SPEED AERODYNAMICS  DOUBLE WEDGE SECTION  WAVE DRAG COEFFICIENT:  LIFT COEFFICIENT:  DRAG DUE .TO LIFT:  LIFT CURVE SLOPE:  CIRCULAR ARC SECTION  WHERE  ( +/c ) = AIRFOIL THICKNESS RATIO  a  2 ANGLE OF ATTACK (IN RADIANS)  M  = MACH NUMBER  Figure 3.73. Approximate Equations for Supersonic Section Characteristics  225 