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首页> 外文期刊>Journal of Computational Physics >An efficient finite differences method for the computation of compressible, subsonic, unsteady flows past airfoils and panels
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An efficient finite differences method for the computation of compressible, subsonic, unsteady flows past airfoils and panels

机译：一种高效的有限差异方法，用于计算可压缩，余弦，不稳定流过翼型和面板

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Abstract A finite differences scheme is proposed in this work to compute in the time domain the compressible, subsonic, unsteady flow past an aerodynamic airfoil using the linearized potential theory. It improves and extends the original method proposed in this journal by Hariharan, Ping and Scott by considering: (i) a non-uniform mesh, (ii) an implicit time integration algorithm, (iii) a vectorized implementation and (iv) the coupled airfoil dynamics and fluid dynamic loads. First, we have formulated the method for cases in which the airfoil motion is given. The scheme has been tested on well known problems in unsteady aerodynamics —such as the response to a sudden change of the angle of attack and to a harmonic motion of the airfoil— and has been proved to be more accurate and efficient than other finite differences and vortex-lattice methods found in the literature. Secondly, we have coupled our method to the equations governing the airfoil dynamics in order to numerically solve problems where the airfoil motion is unknown a priori as happens, for example, in the cases of the flutter and the divergence of a typical section of a wing or of a flexible panel. Apparently, this is the first self-consistent and easy-to-implement numerical analysis in the time domain of the compressible, linearized coupled dynamics of the (generally flexible) airfoil–fluid system carried out in the literature. The results for the particular case of a rigid airfoil show excellent agreement with those reported by other authors, whereas those obtained for the case of a cantilevered flexible airfoil in compressible flow seem to be original or, at least, not we
机译：<！[cdata [ Abstract 在这项工作中提出了有限差异方案，以在时域计算的可压缩，括号，不稳定流过空气动力翼型使用线性化潜力理论。通过考虑：（i）一种非统一网格，（ii）隐式时间集成算法，（iii）耦合的耦合翼型动力学和流体动力载荷。首先，我们制定了用于给出翼型运动的情况的方法。该方案已经在不稳定的空气动力学-SUCH中对众所周知的问题进行了测试，因为响应攻击角度突然变化以及翼型的谐波运动 - 已经被证明比其他有限差异更准确和有效在文献中发现的涡旋晶格方法。其次，我们已经将我们的方法耦合到控制翼型动态的方程，以便在数值上解决翼型运动未知的问题 a先验例如，例如，在案例中振动和翼形或柔性面板的典型部分的分歧。显然，这是在文献中进行的可压缩，线性化耦合动态的时域的第一种自我一致且易于实现的数值分析。对刚性翼型的特定情况的结果表现出与其他作者报道的那些符合良好的一致性，而那些在可压缩流动悬臂的柔性翼型的情况下获得的那些似乎是原始的，或者至少不是我们

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