This is an implementation of the Hess-Smith panel method. The program is capable of plotting the pressure distribution on a NACA 4-digit airfoil and calculating the lift coefficient. It is suitable for basic subsonic aerodynamic analysis. A README file is included for input instructions.
Hess-Smith Panel Method with Data Structures MATLAB Code for Pressure and Lift Coefficient Analysis on NACA 4-Digit Airfoils
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