In aeronautics, wave drag is a component of the aerodynamic drag on aircraft wings and fuselage, propeller blade tips and projectiles moving at transonic and supersonic speeds, due to the presence of shock waves123. At zero angle of attack, the symmetrical airfoil produces no lift. Thus, a positive angle of attack is required if the lift is to be generated. The center of pressure remains relatively constant for a small change in angle of attack
Cdw = Wave drag coefficient of the symmetrical airfoil dW = The wave drag divergence Mach number (the Mach number at which wave drag starts to increase significantly) M = Mach number of the aircraft (flight speed divided by the local speed of sound) α = Airfoil lift curve slope (a measure of how much lift is generated per degree of angle of attack) t = Maximum thickness of the airfoil (perpendicular distance between its upper and lower surfaces) c = Chord length of the airfoil (distance from leading edge to trailing edge)