Find Lift Coefficient of an Arbitrary Airfoil

This program calculates the mean camber line (show in red) from the airfoil drawn, then uses thin airfoil theory to find the lift coefficient.

Instructions: Draw the airfoil within the box provided, where the dashed line is the cord. If you wish to do another airfoil refresh the page. Match to some known airfoils from here to compare results

Compute Learn Theory Github & Usage Example

Created by John Dews-Flick studying at the University of Florida. The results obtained are purely for fun.