CFD Solver for Stationary Flow Analysis around NACA Airfoils

2D Incompressible and Compressible Flow Solver for NACA Airfoils Using Central Difference Finite Discretization and Newton Raphson Algorithm

This CFD code solves numerically the subsonic stationary, 2D, incompressible and compressible flows around NACA airfoils. The code is based on solving the combined Euler equations using the approach of small perturbation theory, using central difference finite discretization and the Newton Raphson algorithm.