JavaFoil - Analysis of Airfoils. JavaFoil is a relatively simple program, which uses several traditional methods for airfoil analysis. The following two methods build the backbone of the program: The potential flow analysis is done with a higher order panel method (linear varying vorticity distribution). Taking a set of airfoil coordinates, it calculates the local, inviscid flow velocity along the surface of the airfoil for any desired angle of attack. The boundary layer analysis module steps along the upper and the lower surfaces of the airfoil, starting at the stagnation point. It solves a set of differential equations to find the various boundary layer parameters. It is a so called integral method. The equations and criteria for transition and separation are based on the procedures described by Eppler [13, 14, 15]. Compared with CalcFoil, this module has been completely rewritten and cleaned up. A standard compressibility correction according to Karman and Tsien has been implemented to take mild Mach number effects into account. As long as the flow stays subsonic (V below V* in the Velocity diagram), the results should be fairly accurate. Usually this means Mach numbers between zero and 0.5. You cannot analyze airfoils in supersonic flow with the methods in JavaFoil.