Analysis demonstrates shock wave and flow separation in airfoils, suggesting implications for aerodynamic design.
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 6×10[6] , and angles of attack 0 to 15 degrees. Note that periodical oscillations were observed at high angles of attack.
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Fujiwara et al. (1986) studied this question.
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