中山大学学报（自然科学版）（中英文）2025，Vol.64Issue(5)：76-83,8.DOI:10.13471/j.cnki.acta.snus.ZR20250103
一种翼身融合体飞机失速特性分析
Analysis of stall characteristics of a blended wing-body aircraft
摘要
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.关键词
翼身融合/失速特性/分离涡模拟/流动特征Key words
blended wing-body/stall characteristics/detached eddy simulation/flow characteristics分类
航空航天引用本文复制引用
胡新科,涂良辉,付建,李镇文..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(5):76-83,8.基金项目
航空科学基金重点项目(2023M006056001) （2023M006056001）
