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 
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