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Large-eddy simulation of laminar transonic buffet. (English) Zbl 1415.76396
Summary: A large-eddy simulation of laminar transonic buffet on an airfoil at a Mach number \(M=0.735\), an angle of attack \(\alpha=4^\circ\), a Reynolds number \(\text{Re}_c=3\times 10^6\) has been carried out. The boundary layer is laminar up to the shock foot and laminar/turbulent transition occurs in the separation bubble at the shock foot. Contrary to the turbulent case for which wall pressure spectra are characterised by well-marked peaks at low frequencies (\(St=f\cdot c/U_\infty\simeq 0.06-0.07\), where \(St\) is the Strouhal number, \(f\) the shock oscillation frequency, \(c\) the chord length and \(U_\infty\) the free-stream velocity), in the laminar case, there are also well-marked peaks but at a much higher frequency \((St=1.2)\). The shock oscillation amplitude is also lower: 6% of chord and limited to the shock foot area in the laminar case instead of 20% with a whole shock oscillation and intermittent boundary layer separation and reattachment in the turbulent case. The analysis of the phase-averaged fields allowed linking of the frequency of the laminar transonic buffet to a separation bubble breathing phenomenon associated with a vortex shedding mechanism. These vortices are convected at \(U_c/U_\infty\simeq 0.4\) (where \(U_c\) is the convection velocity). The main finding of the present paper is that the higher frequency of the shock oscillation in the laminar regime is due to a different mechanism than in the turbulent one: laminar transonic buffet is due to a separation bubble breathing phenomenon occurring at the shock foot.

MSC:
76F65 Direct numerical and large eddy simulation of turbulence
76F06 Transition to turbulence
76K05 Hypersonic flows
76L05 Shock waves and blast waves in fluid mechanics
76N15 Gas dynamics, general
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