Aerodynamic Characteristics of Airfoil Using Panel Method

Potential flow over an airfoil plays an important historical role in the theory of flight. The governing equation for potential flow is Laplace\u27s equation, a widely studied linear partial differential equation. One of Green\u27s identities can be used to write a solution to Laplace\u27s equation as a boundary integral. Numerical models based on this approach are known as panel methods in the aerodynamics community. This paper introduces the availability of a computational tool for constructing numerical modelfor potential flow over an airfoil based on panel methods. Use of the software is illustrated by implementing a specific model using Hess and Smith panel method to compute the flow over a member of the NACA four-digit airfoils