The Beam-Warming scheme was applied to transonic flows around two-dimensional airfoils NACA 0012 and RAE 2822, taking account of the Baldwin-Lomax turbulence model. After appropriate grid generation techniques, the calculation successfully lead to steady flows containing a shock wave and flow separation, for a uniform flow Mach number 0.75, the Reynolds number 6×106 , and angles of attack 0 to 15 degrees. Note that periodical oscillations were observed at high angles of attack.
Fujiwara et al. (Mon,) studied this question.