Under the condition of transonic velocity, shock waves are easy to form on the upper surface of the RAE2822 airfoil, which may cause flow separation under the interaction of shock waves and turbulent boundary layers. This example is also a classic example in NASA V&V for shock wave validation. 

Dimaxer's high-order procedure based on flux reconstruction uses a coarser mesh to prepare the capture of shock wave positions, and the predicted surface pressure coefficient distribution of the blade is close to that of the experiment.

Pictured: RAE2822 airfoil shock results