This lesson covers the concept of the panel method in aerodynamics. It delves into the potential flow past an arbitrary shaped airfoil, discussing the governing partial differential equation, Laplace equation, and its solutions. The lesson also explains the discretization of the airfoil geometry into small pieces, known as panels, and the distribution of vortices on these panels. It further elaborates on the implementation of the Kutta condition and the calculation of pressure and lift per unit span. The lesson concludes with a brief discussion on the limitations of the source-sink approach for non-lifting flows.

- The panel method is a numerical technique used to solve potential flow past an arbitrary shaped airfoil.
- The governing partial differential equation in this context is the Laplace equation.
- The airfoil geometry is discretized into small pieces, known as panels, and vortices are distributed on these panels.
- The Kutta condition must be satisfied to ensure the flow leaves the trailing edge smoothly.
- The pressure and lift per unit span can be calculated based on the strength of the vortices.
- The source-sink approach is limited to non-lifting flows as it cannot model circulation.

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