FOR 1066: Stall Simulation of Wings and Engine Nacelles

运输飞机通常被设计用于需要飞行安全的特定飞行条件范围。与飞行安全相比，飞行性能、运行成本和环境兼容性被认为是次要的价值，但它们在很大程度上取决于飞机的飞行边界。因此，了解运输机在其飞行边界的行为并在确保飞行安全的同时扩展这些边界是非常重要的。虽然实验飞行测试是非常昂贵的，往往是危险的，在数值模拟能力的进步提供了新的视角，飞机设计和飞行测试。限制运输机航程的物理机制之一是机翼和尾翼低速失速。这里需要验证的数学模型和有效的数值算法来进行流场模拟，以计算机翼和尾翼的最大升力及其在失速期间的动态特性。在我们的模拟中将首次考虑气象扭曲的影响。在发动机进气道中具有气流分离的流动状态也很重要，因为由此产生的不均匀进气流可导致风扇级和第一压气机级上的大负载。该研究股致力于建立一个科学的模拟方法，可以解决飞行边界。虽然数值模拟方法现在已经很好地开发了接近飞机设计点的应用程序，并广泛用于工业设计，研究单位将使用跨学科，高保真度的模拟，以解决复杂的相互作用，不同的影响，在失速条件。只有通过密切合作才能应对这一巨大挑战，通过密切合作，才能获得高度精确模拟飞行边界处的外流场和动力发动机短舱所需的科学知识和方法。罗尔斯·罗伊斯德国公司和空中客车德国公司通过提供模型硬件、设施测试时间和用于模型验证的数值模拟资源，参与研究单位的具体转移项目。

Transport aircrafts are generally designed for a specific range of flight conditions where flight safety is required. Flight performance, operational cost and environmental compatibilities are considered secondary values as compared to flight safety, but they depend significantly on the flight boundaries of the aircraft. Therefore, it is of great importance, to know the behaviour of transport aircraft at their flight boundaries and to extend these boundaries while still ensuring flight safety. While experimental flight testing is very expensive and often risky, advances in the numerical simulation capabilities offer new perspectives for aircraft design and flight testing. One of the physical mechanisms that limit the flight range of transport aircrafts is wing and the empennage stall at low speeds. Here one needs validated, mathematical models and efficient numerical algorithms for flow simulation that can be used to compute maximum lift of wings and empennages and their dynamic behaviour during stall. The effect of meteorological distortions will be considered in our simulations for the first time. Flow states with flow separation in the engine inlet are important as well, as the resulting inhomogeneous inlet flow can lead to large loads on the fan stage and the first compressor stages. The Research Unit strives for a scientifically founded simulation methodology that can address flight boundaries. While numerical simulation methods are now well developed for applications close to the aircraft design point and widely used in industrial design, the Research Unit will use interdisciplinary, high fidelity simulations to address complex interactions of different effects at stalling conditions. This great challenge can only met using close cooperation by which scientific knowledge and methods needed for highly accurate simulations of external flow fields and powered engine nacelles at the flight boundaries are obtained. Rolls-Royce Germany and Airbus Germany participate within the Research Unit in specific transfer projects by supplying model hardware, testing time in facilities and resources for numerical simulations used for model validation.