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The present work investigates the ability of the Partially-Averaged Navier-Stokes (PANS) method to reproduce transonic buffet, occurring on airfoils and wings at transonic regime under specific flow conditions. The designed test case for this analysis is the OAT15A unswept wing at Mach number \(\text {M}_{\infty }=0.73\) and Reynolds number \(\text {Re}_c=3\times 10^6\) . The three-dimensional flow is studied by accounting for the wind tunnel walls in the experiments of Jacquin et al. [1]. The computations on a large-span, confined configuration revealed a strong three-dimensionality of the flow both before and after the buffet onset. The comparison with unsteady Reynolds-averaged Navier Stokes (URANS) results showed the benefits of PANS in resolving flow unsteadiness at different flow resolutions, especially on affordable CFD grids, at limited additional cost.

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Numerical Study of Unsteady Shock/Boundary Layer Interaction

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  • 出版模式：

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  • 发表日期：

    2025年

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  • Andrea Petrocchi,
  • Rene Steijl,
  • George N. Barakos

摘要

The present work investigates the ability of the Partially-Averaged Navier-Stokes (PANS) method to reproduce transonic buffet, occurring on airfoils and wings at transonic regime under specific flow conditions. The designed test case for this analysis is the OAT15A unswept wing at Mach number \(\text {M}_{\infty }=0.73\) and Reynolds number \(\text {Re}_c=3\times 10^6\) . The three-dimensional flow is studied by accounting for the wind tunnel walls in the experiments of Jacquin et al. [1]. The computations on a large-span, confined configuration revealed a strong three-dimensionality of the flow both before and after the buffet onset. The comparison with unsteady Reynolds-averaged Navier Stokes (URANS) results showed the benefits of PANS in resolving flow unsteadiness at different flow resolutions, especially on affordable CFD grids, at limited additional cost.