Bending of corner-supported rectangular plate under concentrated load

In this paper the solution for the bending of corner-supported rectangular plate under concentrated load at any point (α/2, η) of the middle line of the plate is given by means of a conception called modified simply supported edges and the method of superposition. Some numerical example is presented. The solution obtained by this method checks very nicely with what was obtained by G.T. Shih^[3] by means of spline finite element method when η=d/2. This shows that this method of solution is satisfactory.     

再入湍流尾迹及其对雷达散射的影响研究

就高超声速再入体尾迹等离子体场而言,为进行其亚密湍流雷达散射截面的理论分析,提出了计算湍流尾迹脉动等离子体场强的理论模型及求解方法,即在研究高超声速尾迹流动特征的基础上,推导、使用包括化学组份浓度脉动强度的k－ε－g湍流模型,用以封闭高超声速粘性尾迹湍流运动时均控制方程组,并用全隐式有限差分法求解,算例小钝锥体的飞行条件为零攻角、M_∞＝21．3,Re_（∞D）＝1．33×10~6;M_∞＝20．5;Re_（∞D）＝3．22×10~5,计算结果得到了合理的参数分布;考虑电磁波在上述等离子体介质中的传播,以单电子多次散射模型─—畸变波Born近似方法,计算了湍流尾迹脉动等离子体雷达散射截面,给出散射能（RCS）在不同极化状态下的分布,分析了散射背景场脉动湍流对电磁波在其中传播的影响．     

圆柱绕流三维不稳定性的低维Galerkin法分析

利用低维Ｇａｌｅｒｋｉｎ方法及Ｆｌｏｑｕｅｔ稳定性分析理论,计算分析了圆柱绕流的三维线性不稳定性．分析中构造了能较好描述尾迹区流动的周向基函数,建立了完备的合理的基函数组,改进了计算机算法．结果证实圆柱二维周期流对展向小扰动为不稳定的,正确地预计了出现三维长波不稳定性的临界雷诺数Ｒｅｃ＝１９０;扰动展向波长为λｃ一３．６ｄ．对雷诺数Ｒｅ为１８０,１９０两种工况下的圆柱三维绕流流场的计算进一步证实了这种流动的整体不稳定性．本文所预计的临界值比Ｎｏａｃｋ等人的结果更为精确,与Ｂａｒｋｌｅｙ等人的ＤＮＳ解一致,与Ｗｉｌｌｉａｍｓｏｎ的实验相符．     

Reissner—Mindlin板模型的关于板厚一致收敛逼近方法

针对Ｒｅｉｓｓｎｅｒ－Ｍｉｎｄｌｉｎ夹支板模型,给出了两个关于板厚一致收敛的稳定给有限元逼近格式,其一,局部特征值摄动法,其二,残差ｂｕｂｂｌｅ－函数法。     

剪切水-气界面下湍流猝发特征的实验研究

利用氢气泡时间线-脉线组合示踪技术定量地考察剪切水-气界面下的湍流猝发现象,分析 猝发事件的信号特征,重点探讨猝发与湍能产生之间的联系. 在猝发过程中,水面近区的瞬 时流速和Reynolds切应力出现较大幅度的脉动,它们在时间和空间垂直方向上表现出高度 的相干性,这是猝发事件的一个显著特征. 在猝发期,猝发事件涉及的空间区域内Reynolds 切应力和湍流脉动强度明显比平均值和非猝发期的情况大. 其结果表明：在所考察的实验 条件下,猝发是剪切水-气界面附近湍流产生的主要过程.     

风电场可靠性模型及其应用

考虑了风速分布的季节性差异和风速的随机变化的影响、风电机组的实际功率特性、风电场尾流效应以及风电机组故障状况,建立了风电场可靠性模型.根据某海上风电场实测数据进行数值仿真实验,结果验证了模型的正确性和有效性.模型为进一步研究大规模风电并网以及风电场功率预测等问题打下了基础.     

AN IMPROVED NAVIER–STOKES PROCEDURE FOR ANALYSIS OF TWO-DIMENSIONAL AEROFOILS IN LAMINAR AND TURBULENT FLOWS

An accurate and robust Navier–Stokes procedure to predict the complex flow about an aerofoil has been developed. Much improvement over existing methods is achieved in various aspects of the solution procedure. The computational grid generated by conformal mapping, which is not only orthogonal but aligned with the inviscid streamlines, keeps the equations simple and minimizes the error due to false diffusion. Formal second-order accuracy is ensured by employing the QUICK scheme for the convective derivatives in the full Navier–Stokes and turbulence transport equations. To treat the separated region properly and to better resolve the flow field in the wake, the two-layer k–ε turbulence model is incorporated. The onset of transition is triggered in a unique fashion to warrant the smooth transition to turbulent flow. Sample calculations for various aerofoil sections show that the prediction is improved substantially over those by existing methods. The details of the flow extending to the wake, such as the surface pressure distribution, C_Lmax, the velocity fields and the Reynolds stress profiles, are found to be in excellent agreement with the data. © 1997 John Wiley & Sons, Ltd.     

The interaction of background ocean air bubbles with a surface ship

A two-fluid model suitable for the calculation of the two-phase flow field around a naval surface ship is presented. This model couples the Reynolds-averaged Navier–Stokes (RANS) equations with equations for the evolution of the gas-phase momentum, volume fraction and bubble number density, thereby allowing the multidimensional calculation of the two-phase flow for monodisperse variable size bubbles. The bubble field modifies the liquid solution through changes in the liquid mass and momentum conservation equations. The model is applied to the case of the scavenging of wind-induced sea-background bubbles by an unpropelled US Navy frigate under non-zero Froude number boundary conditions at the free surface. This is an important test case, because it can be simulated experimentally with a model-scale ship in a towing tank. A significant modification of the background bubble field is predicted in the wake of the ship, where bubble depletion occurs along with a reduction in the bubble size due to dissolution. This effect is due to lateral phase distribution phenomena and the generation of an upwelling plume in the near wake that brings smaller bubbles up to the surface. © 1998 John Wiley & Sons, Ltd.     

A general approach for computing unsteady 3D thin lifting and/or propulsive systems derived from a complete theory

This paper presents the basis of a numerical method for unsteady aerodynamic computation around thin lifting and/or propulsive systems with arbitrary variable geometries, involving the velocity field, the velocity potential, the pressure field and the wake characteristics (geometry and vortex strength). Most of the corresponding theory actually stems from the unsteady wake model established by Mudry, in which the wake is considered to be a median layer, characterized by a pair of functions on which Mudry founded the concept of continuous vortex particle. The governing relations of the continuous problem are then the flow tangency condition, the wake integro‐differential evolution equation, and a flow regularity condition at the trailing edge. This constitutes a rigorous and complete theoretical formulation of this problem, from which a discretization scheme and a numerical method of solution are derived. The view of the vortex wake is similar to the one in the classical vortex lattice approaches, but uses a discrete vortex particle concept, particularly well suited for the prediction of the unsteady wake deformation. This, together with the continuous theory, ensures the computing method compares favorably with the classical methods in terms of flexibility and computing costs. In order to demonstrate the capabilities of the present method, the calculation of flapping wings of variable geometry is also presented. Copyright © 1999 John Wiley & Sons, Ltd.     

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。