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- W2780016891 abstract "The identification of successive stages in the transition of unsteady viscous transonic flow around an aerofoil is carried out by solving the time-dependent Navier–Stokes equations for a compressible fluid in two-dimensional approach. The numerical simulation is carried out at the Mach number range (0.2–0.98). At a fixed Reynolds number (Re=10,000), it is found that this flow undergoes the following four transition steps: It remains steady up to the Mach number values (0.2–0.35) and afterwards it develops spontaneously, without any imposed artificial perturbation, an inherent unsteadiness corresponding to a near-wake von Kármán instability, in the Mach number range (0.35–0.9). It is found that there exists a critical Mach number between the values (0.90–0.95) for which the flow returns to a steady-state. Furthermore, the flow is found to be governed by two instability processes in the Mach number range (0.75–0.8), where, apart from the von Kármán mode (mode I), a lower frequency mode II appears, due to the formation of weakly supersonic alternating zones in the region upstream of the aerofoil, related to the buffeting phenomenon. A triple role played by the increasing compressibility effects to trigger the instability processes, to maintain and to inhibit them in the transonic flow regime is therefore analysed in detail." @default.
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- W2780016891 date "2003-11-01" @default.
- W2780016891 modified "2023-09-25" @default.
- W2780016891 title "Organised modes and shock–vortex interaction in unsteady viscous transonic flows around an aerofoil" @default.
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- W2780016891 doi "https://doi.org/10.1016/s0045-7930(02)00100-7" @default.
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