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Source Panel Method: Airfoil
Source Vortex Panel Method in Python - AE 416 UIUC
![Panel methods [Aerodynamics #11]](https://i.ytimg.com/vi/AGVG2K6R9GA/mqdefault.jpg)
![Vortex Panel Method: Tangential Velocity Geometric Integral [L(ij)]](https://i.ytimg.com/vi/IxWJzwIG_gY/mqdefault.jpg)
![Vortex Panel Method: Normal Velocity Geometric Integral [K(ij)]](https://i.ytimg.com/vi/5lmIv2CUpoc/mqdefault.jpg)
