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首页> 外文期刊>Journal of Aeronautics & Aerospace Engineering >Schneider M (2017) Failure Aeroacoustic’s Investigation on High-Lift Device by using a Modern Hybrid RANS/LES-Model.
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Schneider M (2017) Failure Aeroacoustic’s Investigation on High-Lift Device by using a Modern Hybrid RANS/LES-Model.

机译：Schneider M（2017）使用现代RANS / LES混合模型对高空装置进行了失败的航空声学研究。

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This study focuses on the development, validation and application of the interdisciplinary computational fluid dynamics/computational aeroacoustics (CFD/CAA) method with the name Flight-Physics Simulator AEOLus (FPS- AEOLus). FPS-AEOLus is based on enhanced conservative, anisotropic, hybrid Reynolds-averaged Navier-Stokes/ Large-Eddy Simulation (RANS/LES) techniques to solve an aerodynamic flow field by applying the unsteady, compressible, hyperbolic Navier-Stokes equations of second order. The two-layer SSG/LRR- w differential Reynolds stress turbulence model presented, combining the Launder- Reece-Rodi (LRR) model near walls with the Speziale-Sarkar-Gatski (SSG) model further apart by applying Menter's blending function F,. Herein, Menter's baseline w-equation is exploited for supplying the length scale. Another emphasis is put on the anisotropic description of dissipation at close distance to the solid wall or in wake area for describing the friction-induced surface-roughness behaviour in viscous fluid physics and swirling wake effects. For that purpose, the SSG/LRR-w seven-equations Reynolds stress turbulence model with anisotropic extension was realized, therefor the theory is described in general. Beyond that, a modified delayed detached-eddy simulation (MDDES) and a scale adaptive simulation (SAS) correction to capture the stochastic character of a large-eddy-type unsteady flow with massive flow separations in the broad band is implemented. To demonstrate the time-dependent noise propagation having wave interference a linearized Euler equation (LEE) model using a combined Momentum- and Lamb-vector source have been applied into the CFD/CAA - method. The DLR 15 wing, a High-Lift device in landing configuration having a deployed slat and landing flap is studied experimentally and numerically. The first part of the application deals with the steady flow investigation; however, the same turbulence model is used for the unsteady flow case without the enclosed time derivatives. The second part concentrates on unsteady modelling for the Navier-Stokes and Linearized Euler field. With this new combined CFD/CAA - method, steady and unsteady numerical studies for the high-lift wing configuration for discovering the aerodynamic and —acoustic propagation effects are shown, discussed and when experimental data were available validated. The High-Lift wing has a constant sweep angle of A=30° to investigate possible cross-flow; to realize this, periodic boundary conditions were set in spanwise direction.
机译：这项研究的重点是跨学科计算流体动力学/计算航空声学（CFD / CAA）方法的开发，验证和应用，该方法名为Flight-Physics Simulator AEOLus（FPS-AEOLus）。 FPS-AEOLus基于增强的保守，各向异性，混合雷诺平均Navier-Stokes /大涡模拟（RANS / LES）技术，通过应用二阶非定常，可压缩，双曲Navier-Stokes方程来求解空气动力流场。提出了两层SSG / LRR-w微分雷诺应力湍流模型，通过应用Menter的混合函数F，将壁附近的Launder-Reece-Rodi（LRR）模型与Speziale-Sarkar-Gatski（SSG）模型相结合。在此，利用Menter的基线w方程来提供长度标尺。另一个重点放在各向异性描述上，该描述与固体壁或尾流区域相距很近，以描述粘性流体物理学中摩擦诱导的表面粗糙度行为和旋流尾流效应。为此，建立了具有各向异性扩展的SSG / LRR-w七方程雷诺应力湍流模型，对此理论进行了一般性描述。除此之外，还实施了改进的延迟分离涡流仿真（MDDES）和比例自适应仿真（SAS）校正，以捕获大涡流型非定常流的随机特性，并在宽带中进行大规模流分离。为了证明具有波干扰的时间相关的噪声传播，已将使用动量和兰姆向量源相结合的线性欧拉方程（LEE）模型应用于CFD / CAA-方法。 DLR 15机翼是降落配置中的高举升装置，具有展开的板条和降落襟翼，通过实验和数值研究。该应用程序的第一部分处理稳态流量调查。但是，对于非定常流动情况，没有封闭的时间导数，则使用相同的湍流模型。第二部分集中于Navier-Stokes和线性化Euler场的非稳态建模。通过这种新的CFD / CAA组合方法，可以对高升力机翼构型进行稳态和非稳态数值研究，以发现空气动力学和声传播效应，并进行了讨论，并且可以验证实验数据的有效性。高升程机翼的恒定后掠角为A = 30°，以研究可能的横流。为了实现这一点，在展向方向上设置了周期性边界条件。

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