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Reducing the frictional drag of aircraft is an important issue for realizing a supersonic passenger aircraft. Due to large swept angle of main wing and high Reynolds and Mach numbers, the boundary layer around the swept wing is three-dimensional and laminar-to-turbulent transition is dominated by the crossflow instability near the leading edge. As a passive control device, sinusoidal roughness elements (SREs) are recently found to be effective to suppress this crossflow-induced transition. In this study, we verify whether this SRE device is effective even for supersonic flow and large swept angle. For simplicity, the supersonic Falkner-Skan-Cooke boundary layers are used as base flows on flat plate assuming Mach number 1.5 and swept angles 27 \(^{\circ }\) , 46 \(^{\circ }\) and 65 \(^{\circ }\) . The shape of SRE is optimized for these flows by using direct numerical simulation. The suppression effect and transition delay are successfully observed numerically at swept angles 27 \(^{\circ }\) and 46 \(^{\circ }\) . This result indicates the possibility of applying SREs on the supersonic aircraft’s wing for drag reduction.

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Laminarization of Supersonic Three-dimensional Boundary Layer by Sinusoidal Roughness Elements

  • 章节

  • 发表日期：

    2026年

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  • Makoto Hirota,
  • Shoya Niwano,
  • Yuki Ide,
  • Yuji Hattori,
  • Shigeru Obayashi

摘要

Reducing the frictional drag of aircraft is an important issue for realizing a supersonic passenger aircraft. Due to large swept angle of main wing and high Reynolds and Mach numbers, the boundary layer around the swept wing is three-dimensional and laminar-to-turbulent transition is dominated by the crossflow instability near the leading edge. As a passive control device, sinusoidal roughness elements (SREs) are recently found to be effective to suppress this crossflow-induced transition. In this study, we verify whether this SRE device is effective even for supersonic flow and large swept angle. For simplicity, the supersonic Falkner-Skan-Cooke boundary layers are used as base flows on flat plate assuming Mach number 1.5 and swept angles 27 \(^{\circ }\) , 46 \(^{\circ }\) and 65 \(^{\circ }\) . The shape of SRE is optimized for these flows by using direct numerical simulation. The suppression effect and transition delay are successfully observed numerically at swept angles 27 \(^{\circ }\) and 46 \(^{\circ }\) . This result indicates the possibility of applying SREs on the supersonic aircraft’s wing for drag reduction.