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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.

商用飞机在飞行边界处的行为与复杂的流体物理过程相关联，其特性在实验和数值上都提出了挑战。在大迎角时，机翼上会发生气流分离，从而产生非定常紊流尾流。这些紊流结构向下游传播并与尾翼相互作用。该研究项目的主要重点是研究气流分离、尾流传播及其与尾翼的相互作用，重点是CRM飞机构型和在欧洲跨音速风洞（ETW）中进行的欧盟项目ESWIRP期间对通用CRM飞机构型进行的相关测量。在项目第一阶段的过程中，完成了时间分辨PIV尾流测量的处理。研究了现代尺度分辨数值方法对分离尾流模拟的适用性。实验和数值数据的协同分析提供了对大迎角下大规模分离尾流的形成和行为的见解。对数据集的统计和谱分析表明，数值方法适用于预测尾流中的流动物理和湍流波动，在项目第二阶段，将利用所获得的知识对尾流物理进行深入分析。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。除了第一阶段在大迎角和大分离下进行的研究外，现在还将考虑小迎角，以便分析涉及小尺度流动分离的飞行条件。为此，混合RANS/LES方法适用于这些流动条件将首先确定。方法的具体验证将涉及现有的ESWIRP测量结果以及在申请人部门使用简化配置进行的风洞测量。在前人研究的基础上，分析了尾翼对尾流的影响。为此目的，将在考虑不同的尾翼平面入射角的情况下进行研究，作为参考，不考虑尾翼平面。流体物理学研究将以统计和谱分析以及模态方法（如POD或DMD）为基础，由此将详细检查尾流中的瞬态波动和波动的机翼和尾翼载荷。迎角和尾翼迎角的变化有助于加深对分离尾流的特性及其在各种可能的来流条件下与尾翼的相互作用的理解。