The tutorial simulates two-dimensional, turbulent, compressible, transonic air flow over an idealized airfoil, as shown below. The free-stream Mach number is 0.725 and the angle of attack is 2.54o. This corresponds to RAE2822 case 6 in Reference [1].
The free-stream flow is subsonic, becoming supersonic on the suction side of the airfoil and subsonic again through a shock wave. The lift and drag coefficients are monitored to help determine whether convergence is reached. The final distribution of the pressure coefficient on the airfoil is then compared to experimental data.