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首页> 外文期刊>Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering >Wing flutter simulations using an aeroelastic solver based on the predictor–corrector scheme
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Wing flutter simulations using an aeroelastic solver based on the predictor–corrector scheme

机译：基于预测器-校正器方案的使用气动弹性求解器的机翼颤振仿真

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摘要

An integrated computational fluid dynamics (CFD) and computational structural dynamics (CSD) method is developed here for the calculation and analysis of wing flutter in the time domain. The CFD solver is based on an unsteady multi-grid finite-volume algorithm for the Euler/Navier–Stokes equations on a multi-block structured grid. The CSD solver adopts a linear multi-step method to integrate the aeroelastic governing equations expressed in the modal space. A grid deformation method employing a radial basis function approach is introduced here to generate a dynamically moving grid. The solving procedure of an aeroelastic system is implemented with a predictor–corrector scheme in the physical time. By extrapolating the aerodynamic force, the hybrid predictor–corrector scheme is introduced to save the flow calculation right before the correcting step. The coupled CFD–CSD method is used to simulate wing flutter problems in the time domain in order to predict the stability of an aeroelastic system, which, in this paper, is fulfilled by finding the flutter boundaries. The calculation of the Isogai wing finds an S-shaped flutter boundary, which has been predicted by other studies. The obtained flutter boundary of the AGARD 445.6 wing shows a distinct transonic dip, which agrees well with the experiment result. Computational efficiency and accuracy using two predictor–corrector algorithms and a strong coupling algorithm are also compared.
机译：本文开发了一种集成的计算流体动力学（CFD）和计算结构动力学（CSD）方法，用于时域中机翼颤振的计算和分析。 CFD求解器基于用于多块结构化网格上的Euler / Navier-Stokes方程的非稳态多网格有限体积算法。 CSD求解器采用线性多步法来积分模态空间中表达的气动弹性控制方程。这里介绍一种采用径向基函数方法的网格变形方法来生成动态移动的网格。空气弹性系统的求解过程是在物理时间使用预测器-校正器方案来实现的。通过外推空气动力，引入了混合预测器-校正器方案，以节省校正步骤之前的流量计算。 CFD-CSD耦合方法用于在时域中模拟机翼颤振问题，以预测气动弹性系统的稳定性，本文通过找到颤振边界来实现该稳定性。 Isogai机翼的计算发现了S形的颤动边界，该边界已被其他研究预测。所获得的AGARD 445.6机翼的扑动边界显示出明显的跨音速倾角，与实验结果非常吻合。还比较了使用两种预测校正算法和强耦合算法的计算效率和准确性。

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