Editing Wave drag (section)

=== For double-wedge aerofoil ===
<math>Cd_w = 4 \cdot \frac{\alpha^2 + (t/c)^2}{\sqrt{(M^2 - 1)}}</math><ref name=":0" />

Where:

<math> Cd_w </math> - Coefficient of drag from wave drag

α - Angle of attack

<math> \frac{t}{c} </math> - Thickness to Chord ratio

M - Freestream Mach number


These equations are applicable at low angles of attack (α < 5°)