Physical analysis of interactions between wing wake and tailplane at high-speed stall conditions

高速失速条件下机翼尾流与水平尾翼相互作用的物理分析

• 批准号: 428256106
• 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 Units
• 资助国家: 德国
• 项目状态: 未结题
• 来源: https://gepris.dfg.de/gepris/projekt/428256106?language=en
• 关键词: Physical; analysis; interactions; between; wing

In the first project phase, the influence of the shock-induced separation from the wing on the aerodynamics and loads of the tail plane was investigated for a tandem wing configuration and for the generic XRF-1 transport aircraft configuration. These studies included the characterization of buffet cell propagation and demonstrated the correlation of tail plane load oscillations with turbulent fluctuations in the wake. Aeroelastic effects were not considered, but their impact showed up in the aerodynamic spectra of the wind tunnel measurements, correlating with wing Eigen modes. Furthermore, the XRF-1 configuration with Ultra-High Bypass-Ratio (UHBR) flow-through nacelle was investigated similar to the wind tunnel tests in ETW. An exhaust jet was not considered in the measurements and simulations. Therefore, the goal of this subproject in the second project phase of the FOR 2895 is the investigation of the influence of vibrations of the wing structure on the 3D buffet mechanism and of the influence of an exhaust jet on the interaction of the wake with the tail plane. For this purpose, hybrid RANS/LES simulations of the XRF-1 configuration considering the exhaust jet are performed. Its influence on the separation topology and the near wake is analyzed, and it is determined to what extent the correlation between the buffet on the wing and the turbulence in the wake is altered. Furthermore, it is investigated to which degree the interaction between wake and tail is influenced by the jet. Flow field data extracted from the simulations will additionally be used as inflow data for LES detail simulations of the tail plane in TP5, and the simulation results will be validated with results of the detail simulations from TP5 and TP1. The influence of structural vibrations on the dominant frequencies and propagation characteristics of transonic buffet is analyzed on the XRF-1 and tandem wing configuration using hybrid RANS/LES simulations with imposed vibrations. Furthermore, the influence of the vibrations on the near wake is investigated, and it is determined whether the correlation between the buffet on the wing and the turbulence in the wake is changed, and to what extent a correlation with the vibrations exists. For the tandem wing configuration, the downstream propagation of the wake and its interaction with the tail plane is also analyzed, and it is worked out to which degree the differences in the characteristics of the wake, which are caused by the structural vibrations, have an effect on the wake tail plane interactions. As for the wake investigations on the XRF-1, flow field data extracted from the simulations will be used as inflow data for LES detail simulations of the tail plane of the Tandem wing in TP5, and the simulation results will be validated with these data as well as with measurement data from the Trisonik Wind Tunnel (TP6) and ETW.

在项目的第一阶段，研究了纵列机翼布局和通用XRF-1运输机布局的激波诱导分离对尾翼空气动力学和载荷的影响。这些研究包括抖振单元传播的特性，并证明尾平面载荷振荡与尾流中湍流波动的相关性。没有考虑气动弹性效应，但它们的影响在风洞测量的气动谱中显示出来，与机翼本征模态有关。此外，与ETW中的风洞试验类似，对具有超高马赫数比（UHBR）的流过短舱的XRF-1配置进行了研究。在测量和模拟中未考虑排气射流。因此，在FOR 2895项目的第二阶段，这个子项目的目标是研究机翼结构振动对三维抖振机理的影响，以及排气喷流对尾流与尾翼相互作用的影响。为此，混合RANS/LES模拟的XRF-1配置考虑排气射流进行。分析了它对分离拓扑和近尾流的影响，并确定了它在多大程度上改变了机翼抖振和尾流湍流之间的相关性。此外，还研究了喷流对尾流干扰的影响程度。从模拟中提取的流场数据将另外用作TP 5中尾翼LES详细模拟的流入数据，模拟结果将与TP 5和TP 1的详细模拟结果进行验证。采用混合RANS/LES模拟方法，在XRF-1和串列机翼上分析了结构振动对跨音速抖振主频和传播特性的影响。此外，还研究了振动对近尾流的影响，确定了机翼抖振与尾流紊流之间的相关性是否改变，以及与振动的相关性在多大程度上存在。对于纵列机翼布局，还分析了尾流的下游传播及其与尾翼的干扰，并计算出结构振动引起的尾流特性差异对尾流与尾翼干扰的影响程度。至于XRF-1的尾流研究，从模拟中提取的流场数据将用作TP 5中串列机翼尾翼的LES详细模拟的流入数据，模拟结果将使用这些数据以及Trisonik风洞（TP 6）和ETW的测量数据进行验证。