I've also seen it defined as the lift coefficient of the airfoil chosen so that it matches the airplane lift coefficient. What is the method to calculate a finite wing's lift from its sectional airfoil shape? Pages 152 This equation is simply a rearrangement of the lift equation where we solve for the lift coefficient in terms of the other variables. It is also useful to show the relationship between section lift coefficient and drag coefficient. Be careful if your airfoil is not aligned with the X and Y axis, you have to project the Force. May 18, 2021 at 16:26. = viscosity of the medium. The section lift coefficient is based on two-dimensional flow - the concept of a wing with infinite span and non-varying cross-section, the lift of which is bereft of any three-dimensional effects. Thanks for contributing an answer to Aviation Stack Exchange! There is a rather clever way that aerodynamicists group information about airfoils. window.jQuery || document.write('