Vortex Panel Method for a 2D Airfoil
Excel calculator using vortex panel method for a 2D airfoil. The algorithm is from Kuethe and Chow, Foundations of Aerodynamics, 4th Edition, Wiley (1986). Inputs are coordinate data for the airfoil (from a source such as Abbott and von Doenhoff, Theory of Wing Sections, Dover (1959) and the angle of attack. This being an inviscid flow calculation, the flow will remain attached for any angle of attack. The calculation returns the pressure coefficient Cp as a function of position and a streamline plot.
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