The problem presented in this report is that of finding a method to calculate the lift force from a single-element airfoil of arbitrary shape. A number of restrictions are used in order to simplify calculations while retaining reasonable accuracy. The problem is solved for the two-dimensional case only and no finite-wing effects are taken into account. Furthermore, inviscid and incompressible flow is assumed. The method used to solve the problem is the vortex panel method, with vortex singularities distributed over simplified airfoil geometry.