Study on lift enhancement effectiveness of co-flow jet technology in hybrid wing-body amphibious aircraft
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摘要:
针对翼身混合（hybrid wing-body，HWB）布局水陆两栖飞机设计了单缝富勒襟翼增升装置，在主翼上表面布设了吹吸气区域，系统验证了协同射流（co-flow jet，CFJ）技术对新型气动布局增升效，并对其气动特性提升效果及改善机制进行了阐释。数值模拟结果表明：襟翼偏角为40°时，增升构型最大升力系数达到2.7；布设CFJ后，上翼面流速提高，负压明显增加，翼面初始流动分离得到了有效调控，最大升力系数提高至3.2，失速攻角拓宽4°，阻力系数降低20%以上，俯仰力矩可用范围增加。此外，CFJ也提升了襟翼表面流速，抑制了较大迎角状态下当地的潜在分离，使前缘负压峰值最大提高30%以上，显著提高了襟翼的增升效率。
Abstract:A single-slotted Fowler flap high-lift device for a hybrid wing-body (HWB) configured amphibious aircraft was designed, incorporating blowing/suction zones on the upper surface of the main wing. It systematically validated the lift-enhancement effectiveness of the co-flow jet (CFJ) technology on this novel aerodynamic configuration and elucidated the mechanisms behind its aerodynamic performance improvements. Numerical simulation results demonstrated that: when the flap deflection angle reached 40°, the maximum lift coefficient of the high-lift configuration attained 2.7; after implementing CFJ, the flow velocity over the upper wing surface increased, accompanied by a significant rise in negative pressure. The initial flow separation on the wing surface was effectively controlled, with the maximum lift coefficient increasing to 3.2, stall angle of attack extended by 4°, drag coefficient reduced by over 20%, and available range of pitching moment expanded. Additionally, CFJ enhanced the surface flow velocity on the flaps and suppressed the potential local separation under high angle-of-attack conditions, increasing the leading-edge negative pressure peak by up to 30% and significantly improving the flap lift-enhancement efficiency.
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Key words:
- hybrid wing-body /
- amphibious aircraft /
- single-slotted Fowler flap /
- active flow control /
- co-flow jet
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图 2 HiLiftPW-1构型气动力特性曲线计算与实验结果对比
Figure 2. Comparison of calculated and experimental results for aerodynamic characteristics of the HiLiftPW-1 configuration
图 3 基于NACA0025的CFJ0025-065-196翼型
Figure 3. CFJ0025-065-196 airfoil based on NACA 0025 profile
图 4 CFJ0025-065-196翼段表面网格及空间网格截面
Figure 4. Surface mesh and spatial grid cross-section of the CFJ0025-065-196 wing segment
图 5 CFJ0025-065-196升力特性曲线与30°攻角表面压力系数分布
Figure 5. Lift characteristic curve and surface pressure coefficient distribution at 30° angle of attack for CFJ0025-065-196
图 7 HWB布局水陆两栖飞机浸水面积示意图
Figure 7. Schematic diagram of wetted area for the HWB amphibious aircraft configuration
图 9 中部基本翼型及富勒襟翼翼型
Figure 9. Center basic airfoil and Fowler flap airfoil configuration
图 10 基本翼型及增升翼型升阻特性
Figure 10. Lift and drag characteristics of baseline and high-lift airfoil configurations
图 12 增升构型升阻特性曲线
Figure 12. Lift and drag characteristic curves of high-lift configuration
图 15 CFJ构型气动特性曲线
Figure 15. Aerodynamic performance characteristics of the CFJ configuration
图 16 α=20°增升构型及CFJ构型表面压力系数分布及摩阻系数云图
Figure 16. Surface pressure coefficient distribution and skin friction coefficient contours for high-lift and CFJ configurations at α=20°
图 17 α=22°增升构型及CFJ构型表面压力系数分布及摩阻系数云图
Figure 17. Surface pressure coefficient distribution and skin friction coefficient contours for high-lift and CFJ configurations at α=22°
图 19 α=20°机翼截面压力分布曲线
Figure 19. Pressure distribution curves over wing cross-section at α=20°
图 20 α=22°机翼截面压力分布曲线
Figure 20. Pressure distribution curves over wing cross-section at α=22°
图 21 Y=−11.7 m空间流场截面马赫数分布
Figure 21. Mach number distribution at Y=−11.7 m flow field cross-section
图 22 Y=−13.3 m空间流场截面马赫数分布
Figure 22. Mach number distribution at Y=−13.3 m flow field cross-section
图 23 α=22°襟翼空间流场截面马赫数分布及流线
Figure 23. Mach number distribution and streamlines at flap flow field cross-section at α=22°
图 24 副翼区Y=−20 m空间流场截面马赫数云图
Figure 24. Mach number contour plot at aileron region flow field cross-section of Y=−20 m
表 1 各网格节点分布及网格量
Table 1. Distribution of grid nodes and grid volume
网格类型 网格量/万 展向节点数 流向节点数 密网格 5800 245 485 中网格 2000 173 341 粗网格 700 121 241 
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表 2 吹吸气边界参数
Table 2. Parameters of Injection and Suction Boundary
位置 参数 数值 吹气槽 马赫数Ma 0.26 压比（pt/pref） 1.04 温比（Tt/Tref） 1.011 吸气槽 温比（p/pinf） 0.95
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表 3 水陆两栖飞机模型参数
Table 3. Amphibious aircraft model parameters
参数 数值 全翼展/m 48 机翼面积/m2 216 平均气动弦长/m 4.84 机长/m 39.5
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