Numerical study on the effect of angle of attack on boundary layer transition and aerodynamic heating of the wing-body configuration
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摘要:
为了深入研究攻角对其边界层转捩以及气动热分布的影响规律，提出一种大后掠翼构型的新型翼身组合体外形。采用改进的
k-ω-γ 转捩模式计算了Ma =6不同攻角条件下的边界层转捩情况。研究结果表明：攻角变化对翼身组合体边界层转捩和气动热的影响较为显著，并且壁面的边界层转捩具有从翼身连接处起始，往下游方向，沿连接处向两侧逐渐发展扩大的特点。随着攻角从−10°增大到10°，上表面机身和机翼上的转捩范围的变化趋势均为先减小后增加；下表面机身的转捩范围变化趋势先增加后减小，而机翼上则先减小后增加。并且，翼身组合体迎风面的热流密度分布主要受到边界层转捩作用的影响，而背风面的热流密度分布则受到流动结构和边界层转捩的共同影响。此外，在6°和10°攻角的机翼上表面上发现了流向热流密度条带结构。对比流动结构与热流密度分布发现，热流密度条带的形成与流向涡以及角区流向涡结构的演化有关。Abstract:In order to investigate the influence of angle of attack on boundary layer transition and aerodynamic heating distribution, a novel wing-body configuration featuring a large swept wing was proposed, and the improved
k -ω -γ transition model was used to calculate the boundary layer transition under different angles of attack atMa =6. The research results indicated that variations in the angle of attack significantly affected boundary layer transition and aerodynamic heating of the wing-body configuration, and the boundary layer transition on the surface initiated from the wing-body junction and gradually expanded downstream along the connection, exhibiting a widening trend on both sides. Notably, as the angle of attack increased from −10° to 10°, the transition range on the upper surface of the fuselage and wing initially decreased before increase. On the lower surface, the transition range of the fuselage increased first and then decreased, while on the wing, it decreased first and then increased. As for aerodynamic heating, on the windward side of the wing-body configuration, the heat flux distribution was primarily influenced by the boundary layer transition due to the relatively weak flow structure. On the leeward side, where the flow structure was stronger, the heat flux distribution was affected by both flow structure and boundary layer transition. Additionally, streamwise hot streak structures were identified on the upper surface of the wing at 6° and 10° angles of attack. The comparison between the flow structure and heat flux distribution revealed that the formation of hot streaks was related to the evolution of streamwise vortices and corner stream-wise vortices. -
图 1 翼身组合体外形几何示意图（单位：mm）
Figure 1. Geometric diagram of the wing-body configuration （unit：mm）
图 3 0°攻角下不同网格转捩计算结果与实验结果对比图
Figure 3. Comparison between calculated and experimental results of different grid transitions at 0° angle of attack
图 4 6°攻角下转捩计算结果与实验结果对比图
Figure 4. Comparison between transition calculation results and experimental results at 6° angle of attack
图 5 不同攻角下空间马赫数以及表面压力分布云图
Figure 5. Contours of spatial Mach number and surface pressure distribution at different angles of attack
图 6 不同攻角下转捩计算得到的翼身组合体外形的壁面间歇因子分布
Figure 6. Intermittency factor distribution on the wall of the wing-body configuration obtained from transition model calculations at different angles of attack
图 7 不同攻角下中心线处的热流密度分布
Figure 7. Heat flux distribution along the centerline at different angles of attack
图 8 不同攻角下转捩计算得到的翼身组合体外形壁面的热流密度分布
Figure 8. Heat flux distribution on the wall of wing-body configuration calculated by transition model at different angles of attack
图 9 不同攻角下x=360 mm处的展向热流密度分布
Figure 9. Spanwise heat flux distribution along x=360 mm at different angles of attack
图 10 层流和转捩计算得到的翼身组合体外形下表面壁面热流密度、表面极限流线和流动结构分布
Figure 10. Heat flux, surface limited streamline, and flow structure distributions of the wing-body configuration obtained from laminar flow and transition model calculations on the lower surface
图 11 层流和转捩计算得到的翼身组合体外形上表面壁面热流密度、表面极限流线和流动结构分布
Figure 11. Heat flux, surface limited streamline, and flow structure distributions of the wing-body configuration obtained from laminar flow and transition model calculations on the upper surface
表 1 网格无关性验证的网格分辨率
Table 1. Grid resolution for grid independence verification
网格 网格总量/104 分辨率 y+ 流向 法向 周向 1 2100 561 146 276 0.75 2 1700 511 136 276 1 3 1300 411 126 276 6 
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