Zero Lift Drag Coefficient Calculator

The zero lift drag coefficient, C_D0, quantifies an aircraft’s drag when it produces no lift at zero angle of attack. It’s a dimensionless parameter determined by the body’s shape, surface characteristics, and other non-lift generating factors. Lower C_D0 values signify reduced drag during level flight, enhancing fuel efficiency and overall aerodynamic performance. The formula to calculate Zero lift drag coefficient as follows:

Where:

• C_D​ is the drag coefficient,
• C_D0​​ is the zero-lift drag coefficient,
• C_L​ is the lift coefficient,
• $e$ is the Oswald efficiency factor,
• $AR$ is the aspect ratio of the wings.