Scholarlink

Three-dimensional numerical simulations are performed around the A320 Intermediate Scale (IS) wing prototype of the BEALIVE research project - “Bioinspired Electroactive multiscale Aeronautical Live skin”. The wing has a 70 cm chord and a 59 cm span and is investigated in the subsonic regime at Reynolds number 1 million, Mach number of \(0.063\) and incidence of \(10^\circ\) . Bioinspired electroactive morphing concepts are numerically investigated through vibrations and slight deformations in the near trailing edge region, using the NSMB (Navier Stokes Multi Block) code, the Arbitrary Lagrangian Eulerian method (ALE) method for mesh deformation and the Organised Eddy Simulation (OES) turbulence modelling approach, sensitised to the coherent structures physically correct development. The trailing edge is deformed with a constant vibration frequency and amplitude along the span. The impact of different actuation frequencies in the range \((40\) – \(372) \text{ Hz}\) , corresponding to Strouhal numbers based on the projected chord \((0.23\) – \(2.10)\) are investigated for the same amplitude, \({a}_{p}=0.7\) mm, corresponding to \({a}_{p}/c=0.001\) . Optimal frequencies are found to increase the aerodynamic performance, leading to drag reduction up to \({\sim}4\%\) , lift increase up to \({\sim}3\%\) and lift-to-drag increase up to \({\sim}5\%\) .

错误：搜索内容不能为空，请输入英文关键词
错误：关键词超出字数限制，请精简
高级检索

Three-Dimensional Numerical Simulations Around an A320 Morphing Wing at High Reynolds Number

  • 章节

  • 发表日期：

    2026年

查看全文
  • C. Rouaix,
  • A. Marouf,
  • Y. Hoarau,
  • M. Carvalho,
  • H. Hangan,
  • M. Braza

摘要

Three-dimensional numerical simulations are performed around the A320 Intermediate Scale (IS) wing prototype of the BEALIVE research project - “Bioinspired Electroactive multiscale Aeronautical Live skin”. The wing has a 70 cm chord and a 59 cm span and is investigated in the subsonic regime at Reynolds number 1 million, Mach number of \(0.063\) and incidence of \(10^\circ\) . Bioinspired electroactive morphing concepts are numerically investigated through vibrations and slight deformations in the near trailing edge region, using the NSMB (Navier Stokes Multi Block) code, the Arbitrary Lagrangian Eulerian method (ALE) method for mesh deformation and the Organised Eddy Simulation (OES) turbulence modelling approach, sensitised to the coherent structures physically correct development. The trailing edge is deformed with a constant vibration frequency and amplitude along the span. The impact of different actuation frequencies in the range \((40\) – \(372) \text{ Hz}\) , corresponding to Strouhal numbers based on the projected chord \((0.23\) – \(2.10)\) are investigated for the same amplitude, \({a}_{p}=0.7\) mm, corresponding to \({a}_{p}/c=0.001\) . Optimal frequencies are found to increase the aerodynamic performance, leading to drag reduction up to \({\sim}4\%\) , lift increase up to \({\sim}3\%\) and lift-to-drag increase up to \({\sim}5\%\) .