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This study investigates the Shock-Wave Boundary Layer Interaction (SBLI) around supercritical aerofoils and wings in the Reynolds number range of \((2, 4.5) \times 10^6\) . Physical analysis of the transonic buffet and its interaction with the shear-layer and near wake unsteadiness has been carried out in detail, showing the strong inter-dependence of the SBLI with the downstream unsteadiness. The numerical simulations have been performed with the NSMB—Navier Stokes Multi-Block code, using Delayed Detached Eddy Simulation and Organised Eddy Simulation. Improvement in the aerodynamic forces prediction has been discussed by means of a stochastic forcing approach, based on POD low-energy modes, applied in the DDES simulations around the V2C wing of Dassault Aviation, considering a constant spanwise section. A significant improvement in the aerodynamic performances has been shown and analysed thanks to specific electroactive morphing concepts based on trailing-edge vibration and on travelling waves along the suction side of an A320 morphing prototype. A decrease in the drag reduction in the order of 7% and in lift increase in the order of 3% have been obtained.

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Numerical Study and Physical Analysis of the Transonic Interaction and Its Modification Through Morphing Around Supercritical Wings at High Reynolds Number

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  • 出版模式：

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  • 发表日期：

    2025年

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  • Cesar Jimenez Navarro,
  • Jacques Abou Khalil,
  • Rajaa El Akoury,
  • Abderahmane Marouf,
  • Jean-Baptiste Tô,
  • Yannick Hoarau,
  • Jean-François Rouchon,
  • Marianna Braza

摘要

This study investigates the Shock-Wave Boundary Layer Interaction (SBLI) around supercritical aerofoils and wings in the Reynolds number range of \((2, 4.5) \times 10^6\) . Physical analysis of the transonic buffet and its interaction with the shear-layer and near wake unsteadiness has been carried out in detail, showing the strong inter-dependence of the SBLI with the downstream unsteadiness. The numerical simulations have been performed with the NSMB—Navier Stokes Multi-Block code, using Delayed Detached Eddy Simulation and Organised Eddy Simulation. Improvement in the aerodynamic forces prediction has been discussed by means of a stochastic forcing approach, based on POD low-energy modes, applied in the DDES simulations around the V2C wing of Dassault Aviation, considering a constant spanwise section. A significant improvement in the aerodynamic performances has been shown and analysed thanks to specific electroactive morphing concepts based on trailing-edge vibration and on travelling waves along the suction side of an A320 morphing prototype. A decrease in the drag reduction in the order of 7% and in lift increase in the order of 3% have been obtained.