Purpose

Wingtip loss is an existing type of transport aircraft hazard which is a real threat to flight safety caused by a missile strike, underwing engine explosion or impact with obstructions when performing near-ground operations. The primary effect of the wingtip loss is an asymmetric rolling moment, which may result in the fatal loss of control for the aircraft. This study aims to assess whether aerodynamic degradation will cause a wing-damaged transport aircraft to lose its balance under a certain level of wing damage and if a pilot can compensate for the loss of aerodynamic force and regain the balance of the aircraft.

Design/methodology/approach

In this paper, experimental and numerical studies were conducted to investigate the aerodynamic characteristics of a wingtip-lost transport aircraft in landing configuration. Various levels of wing damages including wingtip, slat and flap loss were considered. The numerical simulations were performed with ANSYS Fluent. The computational fluid dynamics calculation was validated by wind tunnel tests.

Findings

The aerodynamic performance of the aircraft with wing-damaged condition was presented. It was revealed that the wingtip loss leads to an asymmetric rolling moment and a reduction of the lift force, which affects the balance of the transport aircraft. The methods to compensate for the lift force and the asymmetric rolling moment were investigated for a safe landing. The lateral balance cannot be maintained in cases with serious damage on the wing (larger than 53% of the semi-span) or moderate damage on the wing with loss of slats and flaps.

Originality/value

The nonlinear results indicate the importance of aerodynamic assessment for the sake of training pilots to properly handle the hazard situation and explore the critical facts leading to the air crash.

中文翻译：

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机翼受损运输机的空气动力学退化评估

目的

翼尖损失是运输机的一种现有危险，它是导弹打击，机翼下的发动机爆炸或在执行近地操作时遇到障碍物而对飞行安全造成的真正威胁。翼尖损失的主要影响是不对称的侧倾力矩，这可能会导致飞机失控。这项研究旨在评估空气动力学退化是否会导致机翼损坏的运输机在一定程度的机翼损坏下失去平衡，以及飞行员是否能够补偿空气动力的损失并恢复飞机的平衡。

设计/方法/方法

在本文中，进行了实验和数值研究，以研究在降落状态下失去翼尖的运输机的空气动力特性。考虑了各种程度的机翼损坏，包括翼尖，板条和襟翼损失。数值模拟是使用ANSYS Fluent进行的。通过风洞试验验证了计算流体动力学计算。

发现

介绍了机翼损坏状态下飞机的空气动力学性能。结果表明，翼尖损失导致不对称的侧倾力矩和升力的减小，从而影响运输机的平衡。为了安全着陆，研究了补偿升力和不对称滚动力矩的方法。如果机翼受到严重损坏（大于半跨度的53％），或者机翼受到中等程度的损坏而失去板条和襟翼，则无法保持横向平衡。

创意/价值

非线性结果表明，为了培训飞行员正确处理危险情况并探索导致空难的关键事实，进行空气动力学评估非常重要。