On the effects of non-zero yaw on leading-edge tubercled wings

IF 2.9 3区 工程技术 Q2 ENGINEERING, MECHANICAL Advances in Aerodynamics Pub Date : 2024-09-05 DOI:10.1186/s42774-024-00182-4
T. H. New, S. Mandrà
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Abstract

Steady-state numerical simulations were conducted to capture the aerodynamic characteristics and flow patterns resulting from a tubercled and non-tubercled wing subjected to various combined pitch and yaw conditions at $$Re=1.8 \times 10^{5}$$ . Pitch angle ranged from $$0^{\circ }$$ to $$25^{\circ }$$ , while two different yaw angles of $$10^{\circ }$$ and $$30^{\circ }$$ were used. Results show that $$10^{\circ }$$ yaw angle does not impact upon the lift and drag characteristics significantly, while a $$30^{\circ }$$ yaw angle leads to substantial lift and drag losses. Additionally, the tubercled wing continues to confer favourable stall-mitigating characteristics even for the larger yaw angle. Finally, despite skewing the flow structures significantly, the $$30^{\circ }$$ yaw angle also reduces the formations of bi-periodic flow structures, flow separations and recirculating regions along the leading-edge tubercles, suggesting potentially better flow stability and controllability. • Steady-state numerical study is conducted on NACA 634021 baseline and tubercled wings • Two yaw angles of $$10^{\circ }$$ and $$30^{\circ }$$ are used together with pitch angles from $$0^{\circ }$$ to $$25^{\circ }$$ • Results show $$10^{\circ }$$ yaw angle has minimal impact on the lift and drag characteristics, while $$30^{\circ }$$ yaw angle reduces both lift and drag levels significantly • Larger yaw angle leads to more skewed flows, as well as reduced flow separations and recirculating regions • Larger yaw angle also suppresses bi-periodic flow behaviour in tubercled wings, suggesting better flow stability and controllability
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关于非零偏航对前缘块状翼的影响
我们进行了稳态数值模拟,以捕捉在 $$Re=1.8 \times 10^{5}$ 条件下受各种俯仰和偏航组合条件影响的带瘤和不带瘤机翼所产生的气动特性和流动模式。俯仰角从 $$0^{\circ }$ 到 $$25^{/\circ}$,而偏航角为 $$10^{\circ }$ 和 $$30^{\circ }$。结果表明,10^{\circ }$ 的偏航角对升力和阻力特性的影响不大,而 30^{\circ }$ 的偏航角会导致升力和阻力的大幅损失。此外,即使偏航角越大,块根翼仍能保持良好的失速抑制特性。最后,尽管30^{\circ }$$偏航角显著歪斜了流动结构,但也减少了沿前缘小瘤形成的双周期流动结构、流动分离和再循环区域,这表明流动稳定性和可控性可能会更好。- 对 NACA 634021 基准翼和带瘤翼进行了稳态数值研究 - 使用了 $$10^{\circ }$ 和 $$30^{\circ }$ 两种偏航角以及从 $$0^{\circ }$ 到 $$25^{\circ }$ 的俯仰角 - 结果表明 $$10^{\circ }$ 偏航角对升力和阻力特性的影响最小,而 $$30^{\circ }$ 偏航角对升力和阻力特性的影响最大、偏航角越大,流动越倾斜,流动分离和再循环区域越小 - 偏航角越大,还能抑制管状机翼中的双周期流动行为,表明流动稳定性和可控性越好
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来源期刊
CiteScore
4.50
自引率
4.30%
发文量
35
审稿时长
11 weeks
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