The 2-D Euler equations are discretized with a cell-cefltered finite-volume approach and three-stages Runge-Kutta scheme on unstructured triangle mesh. Roe’s characteristicbased flux-difference splitting is used to determine the fiux through the border of control domain. Subcritical and supercritical fiows past NACA OO12 airfoil are calculated to study the convergence, accuracy and efficiency of the algorithm. The results have been validated against structured-grid solutions.
