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首页> 外文会议>Congress of the International Council of the Aeronautical Sciences >AEROELASTIC ANALYSIS OF TYPICAL SECTIONS WITH STRUCTURAL AND AERODYNAMIC NONLINEARITIES
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AEROELASTIC ANALYSIS OF TYPICAL SECTIONS WITH STRUCTURAL AND AERODYNAMIC NONLINEARITIES

机译：结构和空气动力学非线性典型部分的空气弹性分析

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The application of time domain analyses for aeroelastic problem in a transonic flow is considered. The methodology here proposed is to present an investigation on the effects of non-linearities on aeroelastic behavior for an airfoil moving in pitch and plunge. Here structural dynamics is considered in terms of concentrated nonlinearities. The CFD tool employed in the present work is based on the Euler formulation. The governing equations are integrated by cell-centered, finite-volume, centered space discretization and five-stage, hybrid, explicit, Runge-Kutta time marching scheme. This CFD tool solves flows around two-dimensional lifting surfaces moving in pitch and plunge. The computational domain is discretized using unstructured grids and the movement is modeled with dynamic mesh algorithm. To solve the aeroelastic problem the Runge-Kutta method is applied combined with the CFD code. The time domain aeroelastic responses concerned particularly the NACA0012 airfoil are analysed by investigating typical LCO nonlinear effects from phase plane.
机译：考虑了时域分析在跨动力流中的空气弹性问题的应用。这里提出的方法是展示关于非线性对翼型螺距和暴跌移动的翼型空气弹性行为的研究。这里，在集中的非线性方面考虑了结构动态。本作中使用的CFD工具基于欧拉配方。通过以细胞为中心的，有限量，以中心空间离散化和五阶段，混合，明确，跳动-Kutta时间游行方案集成了控制方程。此CFD工具围绕在俯仰和暴跌中移动的二维升降表面周围的流动。使用非结构化网格离散化计算域，并且通过动态网格算法建模移动。为了解决空气弹性问题，使用CFD码应用runge-kutta方法。通过研究来自相面的典型的LCO非线性效应，分析了特别是NaCA0012翼型的时域气动弹性响应。

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