Calculation of lift and drag coefficients for transonic flow over an airfoil is very important for aerospace applications and has been a subject of continued research. The lift and drag coefficients for a NACA 0012 airfoil can be calculated using FLUENT. In the example below, static pressure contours show a stagnation region near the nose and a low-pressure region on the upper surface, indicative of the lift forces at work.

Static pressure contours