尾流激励的叶片气动力降阶模型

气动力降阶模型是研究叶片气动弹性振动快速高效的新方法。现有气动力降阶模型的研究主要集中在叶片颤振方面，没有涉及更为常见的上游尾流激励的叶片振动问题。本文提出基于Volterra级数的尾流激励叶片气动力降阶模型，为尾流激励下叶片振动和动静叶干涉振动研究提供了新的思路。采用行波法简化尾流的参数个数，用阶跃信号法识别降阶模型的核函数。二维叶片的算例结果表明，本文方法可以较准确地描述尾流激励引起的叶片气动力振荡，而且计算效率极高。     

A door to model reduction in high-dimensional parameter space

Model reduction techniques such as Proper Generalized Decomposition (PGD) are decision-making tools that are about to revolutionize many domains. Unfortunately, their computation is still problematic for problems involving many parameters, for which one has to face the “curse of dimensionality”. An answer to this challenge is given in solid mechanics by the so-called “parameter-multiscale PGD”, which is based on Saint-Venant's principle. In this article, a model problem composed of up to a thousand parameters is presented, showing that the method is able to overcome the “curse of dimensionality”.     

Aeroelastic analysis of cantilever plates using Peters’ aerodynamic model,and the influence of choosing beam or plate theories as the structural model

In this paper, the aeroelastic analyses of a rectangular cantilever plate of varying aspect ratio is presented. The classical plate theory has been selected as the structural model. The main point that distinguishes this study from previously reported research is employing Peters’ theory to model aerodynamic effect which is not straightforward. The Peters’ aerodynamic model was originally developed to provide lift and moment, which is only applicable to the structural model based on the beam theories. In this study, using the basic concept of the Peters’ aerodynamic model in addition to utilizing the Fourier series, the pressure distribution is derived, which makes Peters’ model applicable to structural models based on plate theory. This combination provides a much simpler state–space aeroelastic model for plates in comparison to the prevalent panel methods, which could lead to a significant reduction in computational time. In addition, the aeroelastic response of the plate with respect to changes in the structural model from the beam theory to the plate theory is evaluated. By using data from an experiment carried out at Duke University, the theoretical results are evaluated. Furthermore, the differences in structural models obtained from the plate and beam theories can be divided into two distinct parts, which are responsible for differences in bending and torsional behaviors of the structure, separately. This approach enables us to measure the effects of differences of each behavior separately, which could provide with a new insight into the problem. It has been determined that the flutter speeds obtained from the beam and plate aeroelastic models are little affected by the difference in bending behavior, but rather is mainly caused by the difference in torsional frequencies.     

A general modal frequency-domain vortex lattice method for aeroelastic analyses

The generalized aerodynamic force (GAF) matrix is derived for the Unsteady Vortex Lattice Method (UVLM) without the assumption of out-of-plane dynamics. As a result, the approach naturally includes in-plane motion and forces unlike the doublet lattice method (DLM). The derived UVLM GAF is therefore applicable to industry-standard techniques for aeroelastic stability analyses, such as the p–k method. In this work, the fluid–structure interpolation is performed with radial basis functions for surface interpolation. The generalized aerodynamic forces computed with the UVLM are verified against the DLM from NASTRAN on a simple flat plate configuration. The ability of the UVLM to include steady loads is verified with a T-tail flutter case and the results confirm the importance of including steady loads for T-tail flutter analysis. The modal frequency domain VLM therefore provides the same level of efficiency and accuracy than the DLM, but without the restrictions and with the ability to handle complex geometries. It is therefore a viable replacement to the DLM.     

风力机叶片气动噪声的影响参数*

随着风力机的大型化，风电机组对环境的影响不容忽视，必须对风力机气动噪声进行预测和控制。选取基于NACA、DU翼型的某风力机叶片作为研究基准，采用修正BPM半经验模型计算叶片的气动噪声特性，通过改变翼型族、弦长、机组运行状态、风切变指数、来流风向参数，研究叶片外形几何参数、机组运行工况对叶片气动噪声源的影响。计算结果从多个角度总结出水平轴风力机叶片气动噪声的变化规律，为开发高效低噪风电叶片提供参考。     

结合并行策略与距离减缩法的搜索算法及其在CAA中的应用

为提高流场与声场信息传递效率，建立了一种耦合MPI并行策略与改进距离减缩法的搜索算法。在完成点搜索后，采用一种适合于结构和非结构网格的形函数插值算法进行流场插值，实现了流场信息从流场网格到声场网格的快速传递。针对网格点搜索算法效率的验证，选用二维30P30N三段翼为研究对象，在不同的子进程数下进行对比分析。结果表明，相对于传统的距离减缩算法，本文提出的改进算法能有效提高CAA网格点的搜索效率，并且效率随着子进程数的增加而提高。在此基础上，将建立的流场与声场信息传递技术模块应用于CAA方法中，并对二维NACA0012翼型的后缘噪声问题进行计算分析，计算结果反映基于流场与声场信息快速传递算法的CAA方法能有效模拟宽频气动噪声问题。     

开槽对大跨悬挑平屋盖结构风荷载的影响

本文结合一大跨悬挑平屋盖模型的风洞试验研究，分析了此类结构屋盖的平均局部体型系数和极值局部体型系数的分布特性；并根据其风压的分布特性，提出在悬挑屋盖承受较大负压的屋檐和角点附近这些遇强风易发生破坏的部位采取开槽气动抗风措施，进一步研究了该气动抗风措施对大跨悬挑平屋盖结构风荷载的影响，试验结果显示，它们可以有效地削减屋盖风敏感处的风荷载值，使平均局部体型系数大约降低50％，极值局部体型系数大约降低25％，所得的这些结果对于结构的抗风设计有一定的指导意义。     

高速列车外形的气动性能数值计算和头部外形的改进

运用流体力学数值计算软件CFX对我国200km／h电动旅客列车的空气动力性能进行了数值模拟计算，针对列车气动外形存在的问题，对列车头部外形进行了改进，并提出了三种列车头部外形改进方案且对其进行了数值模拟研究。计算结果表明，方案三优于其它两种方案，且较改进前列车的空气动力性能有了较大改善。     

平面叶栅跨音流场气动特性的数值研究

通过对模型方程的分析，给出了一种新的隐格式构造思想。将它运用到关通量分裂格式中，可得到无近似因子分解、无矩阵运算的高效二阶精度隐式矢通量分裂差分格式，并用来直接求解时间平均Ｎａｖｉｅｒ－Ｓｔｏｋｅｓ方程组。数值计算标明：该方法具有精度高、稳定性好、计算量少、收敛快等优点，在平面叶栅跨音流场的计算中，较好地捕获了激波，与实验比较，结果令人满意。     

船舶碰撞的研究方法和进展

本文简要评述船舶碰撞的研究进展和发展趋势．介绍了船舶碰撞研究的内容和方法（包括理论的和实验的）．本文重点阐述实船试验方法，包括实尺试验的基本步骤，实尺试验的输入参数选择和试验地点选择．最后提出了综合性意见，并介绍了国内在碰撞研究方面已做的工作和将要做的工作．