Abstract:
A turbulent transonic flow past two symmetric airfoils with flat midparts is studied numerically. Using the Reynolds-averaged Navier–Stokes equations, we analyze the flow past a 9% thick airfoil with an elliptic nose. A range of the free-stream Mach number $\mathrm{M}_\infty$, in which flow bifurcations occur, is determined. Values of $\mathrm{M}_\infty$ that give rise to significant changes in the lift coefficient with variations of the angle of attack are specified. Flow bifurcations are also revealed for a thin double wedge, i.e., a sort of a hexagon.
Keywords:airfoil, local supersonic regions, buffet, bifurcations.
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