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首页> 外文期刊>The Aeronautical Journal >Improved extrapolation of steady turbulent aerodynamics using a non-linear POD-based reduced order model
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Improved extrapolation of steady turbulent aerodynamics using a non-linear POD-based reduced order model

机译：使用基于非线性POD的降阶模型改进稳态湍流空气动力学的外推法

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摘要

A reduced-order modelling (ROM) approach for predicting steady, turbulent aerodynamic flows based on computational fluid dynamics (CFD) and proper orthogonal decomposition (POD) is presented. Model-order reduction is achieved by parameter space sampling, solution space representation via POD and restriction of a CFD solver to the POD subspace. Solving the governing equations of fluid dynamics is replaced by solving a non-linear least-squares optimisation problem. The method will be referred to as LSQ-ROM method. Two approaches of extracting POD basis information from CFD snapshot data are discussed: POD of the full state vector (global POD) and POD of each of the partial states separately (variable-by-variable POD). The method at hand is demonstrated for a 2D aerofoil (NACA 64A010) as well as for a complete industrial aircraft configuration (NASA Common Research Model) in the transonic flow regime by computing ROMs of the compressible Reynolds-averaged Navier-Stokes equations, pursuing both the global and the variable-by-variable POD approach. The LSQ-ROM approach is tried for extrapolatory flow conditions. Results are juxtaposed with those obtained by POD-based extrapolation using Kriging and the radial basis functions spline method. As a reference, the full-order CFD solutions are considered. For the industrial aircraft configuration, the cost of computing the reduced-order solution is shown to be two orders of magnitude lower than that of computing the reference CFD solution.
机译：提出了一种基于计算流体动力学（CFD）和适当正交分解（POD）的用于预测稳定，湍流空气动力学流动的降阶建模（ROM）方法。通过参数空间采样，通过POD的解决方案空间表示以及CFD求解器对POD子空间的限制来实现模型级简化。通过求解非线性最小二乘最优化问题来代替求解流体动力学的控制方程。该方法将被称为LSQ-ROM方法。讨论了从CFD快照数据中提取POD基本信息的两种方法：全状态向量的POD（全局POD）和部分状态的每个POD（逐变量POD）。通过计算可压缩雷诺平均Navier-Stokes方程的ROM，证明了该方法适用于二维翼型（NACA 64A010）和完整的工业飞机配置（NASA通用研究模型）全局和可变POD方法。对于外推流动条件，尝试使用LSQ-ROM方法。结果与使用Kriging和径向基函数样条法通过基于POD的外推法获得的结果并列。作为参考，考虑了全订单CFD解决方案。对于工业飞机配置，计算出的降阶解决方案的成本比计算参考CFD解决方案的成本低两个数量级。

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  • 来源
    《The Aeronautical Journal》 |2012年第1184期|p.1079-1100|共22页
  • 作者

    R. Zimmermann; S. Goertz;

  • 作者单位

    Institute Computational Mathematics TU Braunschweig Germany;

    Institute of Aerodynamics and Flow Technology German Aerospace Center (DLR) Germany;

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