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Thin Airfoil Panel Method

A numerical technique used to solve the boundary conditions by discretizing the airfoil surface into panels and solving the resulting system of linear equations.
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The statement of the theorem

Discretize the airfoil surface S\mathcal{S} into NN panels. The boundary condition v⃗⋅n⃗=0\vec{v} \cdot \vec{n} = 0 is enforced by solving a system of linear equations for the unknown coefficients (e.g., source/dipole strengths) x\boldsymbol{x}: Ax=b\mathbf{A} \boldsymbol{x} = \mathbf{b} where A\mathbf{A} is the influence matrix derived from the panel geometry and b\mathbf{b} is the prescribed boundary condition vector.