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<p>The blended wing body is a design concept that integrates the fuselage and wing into a continuous structure, significantly reducing aerodynamic drag during flight and improving aircraft fuel efficiency. This study conducts a systematic analysis of the stall characteristics of BWB aircraft, combining numerical simulations and flow field structure analysis to reveal their aerodynamic behavior and stall mechanisms. The detached eddy simulation method is employed, with a delay function introduced for the boundary layer to simulate the full aircraft flow field under different angles of attack and transonic conditions. The study finds that the lift coefficient reaches a peak of 1.9437 at an angle of attack of 35°, after which it decreases due to intensified airflow separation. In transonic flow, strong shock waves in the outer wing region induce increased wave drag and flow separation, while a significant horseshoe vortex system forms at the junction between the central fuselage and outer wing, with vorticity diffusing and dissipating along the spanwise direction. Through analysis of surface pressure and vorticity distributions, the study clarifies the effects of shock-wave boundary-layer interference, three-dimensional flow separation, and vortex system evolution on the stall process, providing critical theoretical insights for BWB layout optimization.</p>

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Study on Transonic Stall Characteristics of a BWB Aircraft

  • 期刊论文

  • 发表日期：

    2026年3月12日

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  • Xinke Hu,
  • Lianghui Tu,
  • Jian Fu,
  • Zhenwen Li

摘要

The blended wing body is a design concept that integrates the fuselage and wing into a continuous structure, significantly reducing aerodynamic drag during flight and improving aircraft fuel efficiency. This study conducts a systematic analysis of the stall characteristics of BWB aircraft, combining numerical simulations and flow field structure analysis to reveal their aerodynamic behavior and stall mechanisms. The detached eddy simulation method is employed, with a delay function introduced for the boundary layer to simulate the full aircraft flow field under different angles of attack and transonic conditions. The study finds that the lift coefficient reaches a peak of 1.9437 at an angle of attack of 35°, after which it decreases due to intensified airflow separation. In transonic flow, strong shock waves in the outer wing region induce increased wave drag and flow separation, while a significant horseshoe vortex system forms at the junction between the central fuselage and outer wing, with vorticity diffusing and dissipating along the spanwise direction. Through analysis of surface pressure and vorticity distributions, the study clarifies the effects of shock-wave boundary-layer interference, three-dimensional flow separation, and vortex system evolution on the stall process, providing critical theoretical insights for BWB layout optimization.