Coefficient of lift to drag ratio calculator

The equation you’ve provided seems to relate the drag coefficient (

C_{d 0}

) to a coefficient

K

and the coefficient of lift (

C_{l}

) for an aircraft or airfoil. It might be part of an aerodynamic analysis or calculation.

$C_{l m d}$ is the coefficient of lift-to-drag ratio.
$C_{d 0}$ is the coefficient of drag when lift is zero (the parasite drag coefficient).
$K$ is a coefficient or factor that relates to the aircraft’s aerodynamic characteristics.