The problem to be simulated is the turbulent flow past a NACA-0012 airfoil. The flow has a free-stream Mach number, M, of 0.55 at an angle of attack, alpha, of 8.34 degrees. The Reynolds number, Re, of the flow, based on the chord length of the airfoil, is 9x10⁶. For this case, the flowfield develops a supersonic bubble near the leading edge of the airfoil upper surface. Furthermore, the flow is slightly separated at the foot of the shock that terminates the supersonic region. For this problem, the k-epsilon turbulence model is employed.