Purpose

The critical Mach number, lift-to-drag ratio and drag force play important role in the performance of the wings. This paper aims to investigate the effect of taper stacking, which has been used to generalize wing sweeping, on those parameters.

Design/methodology/approach

The results obtained are based on steady-state turbulent flowfields computations. The baseline wing is ONERA M6. Various wing planforms are generated by linearly or parabolically varying the spanwise stacking location. The critical Mach number is determined by changing the freestream Mach number for a fixed angle of attack. On the other hand, the analysis of the drag force is carried out by changing the angle of attack to keep the lift force constant.

Findings

By changing the stacking location, the critical Mach number and the corresponding lift-to-drag ratio have increased by around 7 and 3%, respectively. A reduction of 12.8% in total drag force has been observed in one of the analyzed cases. Moreover, there exist some cases in which the values of drag reduce significantly while the lift is the same.

Practical implications

The results of this new stacking approach have implied that the drag force can be decreased without decreasing the lift. This outcome is valuable for increasing the range and endurance of an aircraft.

Originality/value

This work generalizes wing sweeping by modifying the taper stacking along the span. In literature, wing sweep is enhanced using segmented stacking of taper distribution. The present study is further enhancing this concept by introducing continuous stacking (infinite number of stacking segments) for the first time.

中文翻译：

---

锥度堆叠可提高机翼的空气动力学性能

目的

临界马赫数，升阻比和阻力在机翼性能中起着重要作用。本文旨在研究锥化叠加对这些参数的影响，锥化已被用来概括机翼后掠。

设计/方法/方法

获得的结果基于稳态湍流场计算。基线机翼是ONERA M6。通过线性或抛物线改变翼展方向的堆叠位置，可以生成各种机翼平面形状。关键马赫数是通过更改固定攻角的自由流马赫数来确定的。另一方面，通过改变迎角以保持升力恒定来进行阻力的分析。

发现

通过改变堆垛位置，临界马赫数和相应的升阻比分别提高了约7％和3％。在其中一种分析案例中，观察到总阻力降低了12.8％。而且，存在在升程相同的情况下阻力值显着降低的情况。

实际影响

这种新的堆叠方法的结果表明，可以在不减小升力的情况下减小阻力。这一结果对于增加飞机的航程和续航力非常有价值。

创意/价值

这项工作通过修改沿跨度的锥度叠加来概括机翼扫掠。在文献中，使用锥度分布的分段堆叠来增强机翼后掠。本研究通过首次引入连续堆叠（无限数量的堆叠段）进一步增强了这一概念。