Abstract:
A turbulent flow past two symmetric airfoils, whose bow and aft portions are circular arcs, whereas midparts are flat, is studies numerically. The amplitude of lift coefficient oscillations versus the free-stream Mach number $\mathrm{M}_\infty$ is analyzed at zero angle of attack. Ranges of $\mathrm{M}_\infty$ in which there exist flow bifurcations are determined.
Keywords:airfoil, local supersonic zones, shock waves, buffet, bifurcations.
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