小展弦比可控环量翼的风洞试验及其三维效…

本文对一小展弦比（λ＝１）可控环量翼进行了风洞试验，试验结果表明，由于存在着强烈的三维效应，若不采取有效的措施对三维效应进行抑制，则小展弦比可控环量翼三维流动的升力便远远小于二维结果（包括试验与计算）。针对这种情况，本文对小展弦比可控环量民翼的三维效应的抑制做了一些初步探讨。     

二维兴波水翼水动力预报的涡分布法

本文用奇点面分布法预报二维自由面边界下水翼的水动力特性。采用线性化的自由面边界条件。水翼表面划分为若干单元，每个单元上布置线性分布的涡，并在其中点满足Ｎｅｕｍａｎｎ型物面边界条件。与试验结果比较表明，计算结果是合理的，本计算方法能显示二维兴波水翼水动力特性与Ｆｒｏｕｄｅ数，相对浸深和攻角的关系。     

沟灌二维入渗参数的影响因素与计算模型研究

为简化沟灌二维入渗参数的获取,本文以室内入渗试验为基础,分析了土壤容重、初始含水量、入渗水头这三个因素对二维和一维入渗参数参数比值的影响,初步建立了由一维垂直入渗参数推求二维入渗参数的多因子计算模型,并对模型分析简化,增加了模型的稳健性,通过大田试验对所建计算模型进行检验。结果表明文中所建二维入渗参数计算模型所求结果为整个灌水田块的均值,其与整个田块全部灌水沟由水流运动数据推求的入渗参数平均值误差不大,且入渗参数k、a增减相反,对累积入渗量的计算结果影响较小,说明本文所建模型对精度要求不高的沟灌灌水方案设计具有一定的指导意义。     

三维薄翼入水水动力的计算

本文提供了一个计算三维薄翼高速入水水动力性能的非定常数值升力面方法。假设薄翼高速入水时,翼的背面为全空泡状态,当翼的随边进入液面后,此空泡域按一定的方向拖至自由液面。在翼的拱弧面上布置线涡和线源,在翼后空泡面上布置线源,所有的奇点系在自由液面上方存在映象以满足自由液面条件。根据翼迎流面的法向不可穿透条件和翼背面及翼后空泡面上的空泡动力学条件确定所有待定线涡和线源的强度,并由此可以计算各时刻翼上压力分布。利用本文提供的方法首先计算了二维薄翼入水的水动力性能,将结果与理论解进行比较,两者结果较为一致。然后,研究了三维薄翼的入水问题。     

水跃紊流特性的数值研究

本文采用直接解N-S方程式和标准的K-ε紊流模型方程式的方法,对二维强迫水跃和淹没水跃进行了数值模拟计算;给出了水跃在不同时刻自由表面的形状、流速及紊流输运量的变化,并和文献[1]的二维激光测速仪的实测结果进行比较,计算结果能较好地与试验结果相吻合。     

确定裂隙岩体渗透系数张量的一维环单元模型研究

裂隙岩体的渗透张量确定一直是渗流领域研究的重点。本文基于广义达西定律,提出一种新型空间一维环单元模型来计算三维裂隙岩体的渗透张量,该模型简化了以往复杂的三维面状流模型。通过解析法和数值模拟法对一维环单元模型的合理性进行验证,并利用面单元模型校核该模型的精度。结果表明：对于同一裂隙岩体,环单元模型计算得到的渗透张量,与现场压水试验校核过的数据相比,误差在合理范围之内,与面单元模型计算得到的结果相比,基本相同;环单元模型是一种可行、精度高且实用的简化模型,比面状流模型简单,在计算渗透张量时能极大地减小运算规模,优化了算法。研究成果可为确定裂隙岩体的渗透张量提供新思路。     

偏心环空层流螺旋流动的近似解析解

本文分析计算了石油钻井工程偏心环空中内管转动的螺旋流动，将偏心环空的三维流动简化为环空薄层内的二维流动，从黎曼空间曲面张量表达的动量方程出发，求得了偏心环空层流螺旋流动速度的近似解析解。用此方程的同心环空表达式与精确解比较，精度较高。     

鱼翅推进

本文对一种鱼类的三维不定常运动提出了一个计算方法。此方法是计算飞机气动力时常用的Woodward方法(定常运动)的一个发展。不同处主要在两个方面:1)物面边界条件:除原有的法向速度外,还要考虑鱼翅本身运动(周期运动)的法向速度分量。2)计及尾涡的变化,尾涡面除原有均匀分布的分量以外,还有周期变化的分量。整个问题以涡的形式来处理。求出涡的分布,则运动的所有参数均可积分得到。 作为例子,本文计算了有攻角的矩形翼的突然起动和椭圆翼的扑舞运动。前者所得的涡量分布和二维平板翼的压力分布相同,由此可知计算方法无误。而由后者计算所得的物理图象与实际是符合的。 本文所发展的方法可以应用在设计“减摇鳍”等一类工程实际问题中。     

对二维翼空化流动的数值模拟

应用二维不可压缩N-S方程结合改进VOF空化模型模拟了NACA66二维翼的空化流动.数值计算中采用SST k-ω湍流模型计算了不同空泡数下定常稳态空化发生时水翼吸力面的压力分布,并与实验结果进行对比,发现空化末端压力梯度计算值明显大于实验值,而且压力有明显突增,通过修正空化模型中的经验参数较好地解决了这个问题.应用SST-SAS湍流模型及修正的经验参数较好地模拟了低空泡数时非定常云空泡的脱落现象,该数值方法对非稳态空化的发展,脱落过程及其频率的预报结果与实验结果吻合良好.     

二维计算程序在张力式平台研究中的应用

本文借助二维势流理论计算程序CSR2计算了张力式平台(TLP)的波频响应,并与中国船舶科学研究中心耐波性水池规则迎浪、斜浪中的试验结果及三维计算程序CSR3的计算结果进行了比较,为进一步验证该程序的可靠性,与荷兰船模水池TLP的三维理论计算及船模试验结果进行了对比,诸结果表明:该二维程序在波频范围内用于估算TLP的波频响应可以给出满意的结果。     

NUMERICAL STUDIES ON THE PROPULSION AND WAKE STRUCTURES OF FINITE-SPAN FLAPPING WINGS WITH DIFFERENT ASPECT RATIOS

An immersed-boundary method is used to investigate the flapping wings with different aspect ratios ranging from 1 to 5. The numerical results on wake structures and the performance of the propulsion are given. Unlike the case of the two-dimensional flapping foil, the wing-tip vortices appear for the flow past a three-dimensional flapping wing, which makes the wake vortex structures much different. The results show that the leading edge vortex merges into the trailing edge vortex, connects with the wing tip vortices and then sheds from the wing. A vortex ring forms in the wake, and exhibits different patterns for different foil aspect ratios. Analysis of hydrodynamic performances shows that both thrust coefficient and efficiency of the flapping wing increase with increasing aspect ratio.     

NUMERICAL STUDY OF FLOW PAST AN AXISYMMETRIC BODY WITH A RING WING AT VARIOUS ATTACK ANGLES

1 .　INTRODUCTIONFortraditionalbody fittedgridsystemusedtocomputetheflow pasttheaxisymmetricbody ,thesingularityonthelongitudinalaxisisalongstand ingobstacle .Rationalsolutionishardtobeachievedevenwithfinemeshesgeneratedwithinthevicinityofthelongitudinalaxis .Hence ,appro priategridsystemisreguiredtoavoidthesingulari ty .Extensivenumericalexperimentsareconductedtoobtainthedesired gridsysteminthis paper .BasedontheideaofDDM[1] ,theoriginalflowfieldofthebodyisdividedinto 8sub domainsac cor…     

EXPERIMENTAL AND NUMERICAL STUDY FOR HYDRODYNAMIC CHARACTERISTICS OF AN OSCILLATING HYDROFOIL

The present article reports the experimental Particle Image Velocimetry （PIV） investigation and the corresponding numerical simulation results about the water flow over the oscillating hydrofoil and its unsteady dynamic characters. The experimental study focuses on the effect of mean angles of attack. The comparison between the PIV results and numerical prediction about the flow field using Fluent well demonstrates the capability of CFD on the simulation of the water flow around the pitching hydrofoil. The numerical results indicate that the forced oscillating frequencies have evident effects on the flow separation and vortex shedding. The simulations about the hydrodynamic drag and lift coefficients were also performed.     

Performance of the bio-inspired leading edge protuberances on a static wing and a pitching wing

It is shown that the leading edge protuberances on the flippers of a humpback whale can significantly improve the hydrodynamic performance. The present study numerically investigates the flow control mechanisms of the leading edge protuberances on a static wing and a pitching wing. For static wings, the performance in both laminar flow and turbulent flow are studied in the context of the flow control mechanisms. It is shown that the protuberances have slight effects on the performance of static wings in laminar flow. Also, it could be deduced that non-uniform downwash does not delay the stall occurrence in either laminar flow or turbulent flow. In turbulent flow, the leading edge protuberances act in a manner similar to vortex generators, enhancing the momentum exchange within the boundary layer. Streamwise vortices do contribute to the delay of the stall occurrence. The normal vorticity component also plays an important role in delaying the stall occurrence. However, for the pitching wing, the effect of leading edge protuberances is negligible in turbulent flow. Detailed analysis of the flow field indicates that for the wing with the leading edge protuberances, the leading edge vortices become more complex, while the thrust jet and the vortices in the wake are not changed significantly by the leading edge protuberances.     

不等直径串列圆柱绕流大涡模拟

为研究背负式海底管线中增设的小直径附属管线对主管线的水动力影响,将大涡模拟中经典Smagorinsky亚格子模型与特征线算子分裂有限元法结合,并引入出口对流边界条件,完善了基于特征线算子分裂有限元的大涡模拟方法。通过自编程序数值模拟Re=1 000的单圆柱绕流,计算结果与相关文献吻合较好,验证了该算法计算圆柱绕流的有效性,并分析了Re=1 000时不同直径比、间距比情况下的串列双圆柱绕流,根据流场的不同涡脱落形态及两圆柱平均阻力系数、升力系数随直径比、间距比变化的规律得到了不同直径比条件下的临界间距范围。达到临界间距后,流场由单一涡脱落状态转变为双涡旋脱落状态。最后分析了两圆柱平均阻力系数及升力系数在临界间距后急剧增加的原因,为背负式海底管线的布局优化提供了理论依据。     

低雷诺数下的钉螺绕流特征数值模拟

研究钉螺在水流中的运动规律对于控制钉螺扩散具有十分重要的意义。通过开源流体力学计算软件OpenFOAM,使用非结构化的三角形网格拟合钉螺边界,采用有限体积法和PISO算法计算平面无限区域中黏性不可压缩流体下的钉螺绕流运动,模拟了低雷诺数下横向和纵向2种水流条件螺体后方尾流形态变化,详细描述了漩涡脱落过程等现象;对比分析不同条件下钉螺的阻力系数C_D、回流区长度L_w/D、斯特罗哈数St等的区别。研究结果表明:随着雷诺数的增加,钉螺的阻力系数逐渐减小,尾流形态呈现3种不同的形态,初步确定各流态转变的临界雷诺数的范围。该研究可为进一步掌握钉螺扩散规律、改进水利阻螺措施提供理论依据。     

高雷诺数下双圆柱绕流的数值模拟

本文使用表面涡法研究高雷诺数下不同排列方式双圆柱绕流的流动状态，计算了双圆柱在并列、串列及级列的情况下的各种流动结构，涡街的变化及作用在圆柱上的受力情况。本文结果清楚地描述了双圆柱绕流复杂的流动状况，计算结果与实验显示的流动状况十分相似，斯特罗哈数和阻力系数与实验结果符合得很好。     

CALCULATION OF VISCOUS FLOW AROUND CIRCULAR CYLINDER WITH THREE-DIMENSIONAL NUMERICAL SIMULATION

1 .　ＩＮＴＲＯＤＵＣＴＩＯＮＴｈｅｆｌｏｗａｒｏｕｎｄａｃｉｒｃｕｌａｒｃｙｌｉｎｄｅｒｉｓｖａｌｕａｂｌｅｉｎｏｉｌｃｏｍｐａｎｉｅｓｏｒｏｆｆｓｈｏｒｅｉｎｄｕｓｔｒｙｔｈａｔｒｅｌｙｉｎｍｏｓｔｃａｓｅｓｏｎｓｕｂｓｅａｐｉｐｅｌｉｎｅｏｒｒｉｓｅｒｓｔｏｔｒａｎｓｐｏｒｔｇａｓａｎｄｏｉｌｆｒｏｍｏｃｅａｎｇｒｏｕｎｄｓｔｏｌａｎｄｏｒｓｕｒｆａｃｅｐｌａｔｆｏｒｍ .Ｗｅｓｈｏｕｌｄｅｎｓｕｒｅｔｈａｔｔｈｅｓｅｏｆｆｓｈｏｒｅｓｔｒｕｃｔｕｒｅｓａｒｅｒｅｓｉｓ ｔａｎｔａｎｄｓｔａｂ…     

湍流中泥沙垂线分布的力学解释

作者从泥沙垂向动量交换出发，分析了泥沙在紊流中由于湍流脉动产生的升力效应，并综合考察了非湍流脉动原因存在的升力以及在不同浓度下含沙水流中泥沙受到的有效重力，得到了基于力学角度的泥沙浓度垂线分布的关系式。在此基础上，通过对床面粗糙度、泥沙粒径和含沙量等影响泥沙浓度垂线分布有关因素的分析，探讨了挟沙水流中两种不同浓度分布类型产生以及转化的原因，并结合具体的试验资料对泥沙浓度垂线分布形态时行了计算和验证，取得了较好的结果。     

Numerical simulation of wave interacting with a submerged cylinder using a 2D RANS model

A 2D RANS numerical model (IH2VOF) is employed to study wave interacting with a circular cylinder with a diameter of 0.02 m in a water depth of 0.27 m, with a wave period of 1.08 s and a wave height of 0.047 m. The influence of the wall proximity on the forces is analyzed for ratios between the pipe (i.e. circular cylinder) distance from the bottom and the pipe diameter varying from 0.04 to 1.5. Results of lift forces and streamlines are compared with the experimental results of Jarno-Druaux et al. (1995) and good agreement is found. Lift, drag and inertia coefficients are also compared with experimental results and the same trend of fundamental quantities with the gap between the cylinder and the bottom was obtained with the model giving slightly larger values. Finally, the influence of the method to estimate the drag and inertia coefficients in the force calculated using Morison equation is analyzed and Morison method shows the better agreement.