Distribution of singularities such as sources, sinks and vortices is the one of the analytical procedures to determine the flow around an airfoil.
The integral equations involving such singularity distribution can be solved only for flow over bodies of simple geometry. Thus, for flow around bodies of arbitrary geometry only numerical solutions are feasible.
In this thesis, the computational procedure for the numerical solution of this integral equation by Fourier-series expansion is presented to evaluate lift and pitching moment applied to the proper airfoil.
A good agreement is reached between the analytical data obtained by the numerical procedure and by other pertinent available analyses.
The advantages of the presented computational procedure are computing time is short involving smaller number of terms yet produces the realiable data for stagnation, maximum and minimum velocity regions also.