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FOR 1066: Stall Simulation of Wings and Engine Nacelles

FOR 1066：机翼和发动机短舱的失速模拟

基本信息

批准号：
62584147
负责人：
金额：
--
依托单位：
Institut für Strömungsmechanik
依托单位国家：
德国
项目类别：
Research Units
财政年份：
2008
资助国家：
德国
起止时间：
2007-12-31 至 2014-12-31
项目状态：
已结题

来源：
https://gepris.dfg.de/gepris/projekt/62584147?language=en
关键词：
1066 Stall Simulation Wings Engine

项目摘要

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.

运输飞机通常是为需要飞行安全的特定飞行条件范围而设计的。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上的行为，并在保证飞行安全的情况下扩展这些边界是非常重要的。虽然实验飞行测试非常昂贵且往往有风险，但数值模拟能力的进步为飞机设计和飞行测试提供了新的视角。限制运输机飞行距离的物理机制之一是机翼和尾翼在低速时失速。在这里，人们需要经过验证的数学模型和有效的流动模拟数值算法，可以用来计算机翼和尾翼的最大升力及其失速时的动态行为。我们将首次在模拟中考虑气象畸变的影响。发动机进气道内流动分离的流动状态也很重要，因为由此产生的不均匀进口流动可能导致风扇级和压气机一级的大负荷。研究单位努力寻求一种科学的模拟方法，可以解决飞行边界问题。虽然数值模拟方法现在已经很好地应用于接近飞机设计点的应用，并广泛应用于工业设计，但研究单位将使用跨学科的高保真模拟来解决失速条件下不同影响的复杂相互作用。这一巨大的挑战只能通过密切合作来解决，通过这种合作，才能获得高度精确模拟飞行边界外流场和动力发动机舱所需的科学知识和方法。劳斯莱斯德国公司和空客德国公司通过提供模型硬件、设备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。