Lift coefficient
= Lift coefficient
{title2=$C_L=L/(q_\infty S)$}
The signed <lift> divided by <dynamic pressure> times a stated reference area. For a two-dimensional <airfoil>, use $c_l=L'/(q_\infty c)$ instead. Reference area and experimental flow conditions are part of the definition of a reported coefficient; see <lift> for a worked scale and a pressure/balance experiment.