Two-dimensional flow solver with GUI using vortex particle and boundary element methods

This repository makes use of the Vortex Panel Method to calculate the Lift, Drag and Pressure Coefficients of any airfoil at a specified Freestream Velocity, Chord Length and Angle of Attack by providing the X and Y coordinates of the airfoil in a .dat file.

The main objective of this project is to create a MATLAB code using Vortex Panel Method to compute pressure coefficient, tangential velocity and aerodynamic forces of given object.