Analysis of stall characteristics of a blended wing - body aircraft

HU Xinke; TU Lianghui; FU Jian; LI Zhenwen

doi:10.13471/j.cnki.acta.snus.ZR20250103

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Analysis of stall characteristics of a blended wing - body aircraft

Research articles | 更新时间：2025-11-14

- Analysis of stall characteristics of a blended wing - body aircraft
- Acta Scientiarum Naturalium Universitatis Sunyatseni Vol. 64, Issue 5, Pages: 76-83(2025)
- 作者机构：
  
  南昌航空大学航空宇航学院，江西南昌 330063
- 作者简介：
- 基金信息：
- DOI：10.13471/j.cnki.acta.snus.ZR20250103
  CLC： V212.1
- Received：01 June 2025，
  
  Accepted：13 June 2025，
  
  Published Online：07 July 2025，
  
  Published：25 September 2025
- 稿件说明：
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胡新科,涂良辉,付建等.一种翼身融合体飞机失速特性分析[J].中山大学学报(自然科学版)(中英文),2025,64(05):76-83.

HU Xinke,TU Lianghui,FU Jian,et al.Analysis of stall characteristics of a blended wing - body aircraft[J].Acta Scientiarum Naturalium Universitatis Sunyatseni,2025,64(05):76-83.
胡新科,涂良辉,付建等.一种翼身融合体飞机失速特性分析[J].中山大学学报(自然科学版)(中英文),2025,64(05):76-83. DOI： 10.13471/j.cnki.acta.snus.ZR20250103.

HU Xinke,TU Lianghui,FU Jian,et al.Analysis of stall characteristics of a blended wing - body aircraft[J].Acta Scientiarum Naturalium Universitatis Sunyatseni,2025,64(05):76-83. DOI： 10.13471/j.cnki.acta.snus.ZR20250103.

摘要

针对翼身融合体飞机的失速特性，结合数值模拟与流场结构解析，揭示其气动行为与失速机制。采用分离涡模拟并在边界层引入延迟函数，对不同迎角、跨音速条件下的整机流场进行仿真。研究发现，翼身融合体飞机升力系数在迎角为35°时达到峰值1.943 7，随后因气流分离加剧而下降。跨音速流动中，外翼区域的强激波引发波阻增大与流动分离，中央机身与外翼结合部形成显著的马蹄涡系，涡量沿展向扩散耗散。通过表面压力与涡量分布分析，阐明了激波—边界层干扰、三维流动分离及涡系演化对失速过程的影响，为翼身融合体飞机布局优化提供了关键理论依据。

Abstract

This study conducts a systematic analysis of the stall characteristics of BWB aircraft， combining numerical simulation with flow field structure analysis to reveal their aerodynamic behavior and stall mechanisms. The detached eddy simulation method is adopted， and a delay function is introduced for the boundary layer to simulate the full aircraft flow field under different angles of attack and transonic conditions. This study finds that the lift coefficient reaches a peak of 1.943 7 at an attack angle of 35°， followed by a decline 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 of the central fuselage and outer wing， with vorticity diffusing and dissipating along the spanwise direction. Through the analysis of surface pressure and vorticity distribution， the influence of shock wave-boundary layer interaction， three-dimensional flow separation， and vortex system evolution on the stall process is clarified， providing key theoretical basis for the layout optimization of BWB aircraft.

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references

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