Studies on the Development of Massively Separated Wakes of Aircraft

飞机大规模分离尾流的发展研究

基本信息

批准号：
314807291
负责人：
Dr.-Ing. Thorsten Lutz
金额：
--
依托单位：
Institut für Aerodynamik und Gasdynamik (IAG)
依托单位国家：
德国
项目类别：
Research Grants
财政年份：
2016
资助国家：
德国
起止时间：
2015-12-31 至 2021-12-31
项目状态：
已结题

来源：
https://gepris.dfg.de/gepris/projekt/314807291?language=en
关键词：
Studies Development Massively Separated Wakes

项目摘要

The behavior of commercial aircraft at the flight boundaries is associated with complex fluid-physical processes, the characterisation of which presents a challenge both experimentally and numerically. Flow separation occurs on the wing at high angles of attack, resulting in an unsteady turbulent wake. These turbulent structures are propagated downstream and interact with the tail plane. The main focus of this research project is the study of the interaction between flow separation, wake propagation and its interaction with the tail plane.The project focuses on the CRM aircraft configuration and associated measurements carried out during the EU project ESWIRP in the European Transonic Wind Tunnel (ETW) on the generic CRM aircraft configuration. During the course of the first project phase, the processing of time-resolved PIV wake measurements was completed. The suitability of modern scale-resolving numerical methods for the simulation of separated wake flows was investigated. Synergetic analyses of the experimental and numerical data have provided insights into the formation and behavior of massively detached wake flows at high angles of attack. Statistical and spectral analyses of the data sets have shown that the numerical methods are suitable for the prediction of the flow physics and the turbulent fluctuations in the wake.In the second project phase, the gained knowledge will be used to carry out in-depth analyses of the wake physics. The first step is to examine to what extent the differences between the computational and experimental studies influence the comparability of the results. In addition to the investigations carried out in the first phase at a high angle of attack and massive separation, smaller angles of attack will now also be considered in order to analyze flight conditions involving a smaller scale flow separation. To this end, hybrid RANS/LES methods suitable for these flow conditions will be identified first. Specific validation of the methods will involve both the existing ESWIRP measurement results and, in addition, wind tunnel measurements carried out at the applicant's department using a simplified configuration. Based on previous findings, the influence of the tail plane on the wake will be analyzed. For this purpose, investigations will be carried out under consideration of different tail plane incidence angles and, as a reference, without the tail plane. Fluid physics studies will be based on statistical and spectral analyses as well as modal methods such as POD or DMD, whereby both the transient fluctuations in the wake and the fluctuating wing and tail plane loads will be examined in detail. The variations of the angle of attack and tail incidence serve to obtain an enhanced understanding of the behaviour of the separated wake and its interaction with the tail over a wide range of possible inflow conditions.

飞行边界上商用飞机的行为与复杂的流体物理过程有关，其表征在实验和数值上都提出了挑战。流动分离以高攻击角在机翼上发生，导致不稳定的湍流唤醒。这些湍流结构在下游繁殖并与尾巴相互作用。该研究项目的主要重点是研究流动分离，唤醒繁殖与与尾平面的相互作用之间的相互作用。该项目重点介绍了欧洲跨性别风隧道（ETW）在通用CRM飞机上的欧盟ESWIRP期间进行的CRM飞机配置和相关测量。在第一个项目阶段的过程中，完成了时间分辨PIV唤醒测量值的处理。研究了现代化量表的数值方法对分离尾流的模拟的适用性。对实验数据和数值数据的协同分析为高度攻击角度的大规模分离尾流流的形成和行为提供了见解。数据集的统计和光谱分析表明，数值方法适用于唤醒中流动物理学和湍流波动的预测。在第二个项目阶段，获得的知识将用于对尾流物理学进行深入分析。第一步是检查计算和实验研究之间的差异在多大程度上影响结果的可比性。除了在第一阶段进行的调查以高攻击角度和大规模分离进行，现在还将考虑较小的攻击角度，以分析涉及较小规模流量分离的飞行条件。为此，将首先确定适合这些流动条件的混合架/LES方法。该方法的具体验证将涉及现有的ESWIRP测量结果，此外，还使用简化的配置在申请人部门进行了风洞测量。根据先前的发现，将分析尾平对尾流的影响。为此，将考虑不同的尾巴射击角度，作为参考，无需尾巴平面。流体物理学研究将基于统计和光谱分析以及模态方法，例如POD或DMD，从而详细检查了尾流的瞬态波动以及波动的机翼和尾平的载荷。攻击角度和尾部入射角的变化可以增强对分离唤醒的行为及其与尾巴相互作用的理解，并在广泛的可能的流入条件下。