层流介质中金属板腐蚀电位分布研究

为了研究流动介质中产生的静电场,结合电化学和流体力学相关知识建立层流介质中金属板模型,利用贝塞尔函数展开及其逆运算推导出在三层介质中基于点电荷模型的腐蚀电位解析表达式,同时计算出金属板产生的电场。运用推导出的解析表达式计算出在流动介质中任意场点处金属板随不同流速产生的腐蚀电位,并通过实验验证结果的正确性。结果表明,对层流条件下电化学反应产生的电流密度所建模型的结果与实验测量数据吻合度较高,同时电场分布也会随着流体流速及层流方向上长度的变化而发生变化。     

收缩管道装置层流热边界层理论及应用研究

研究了收缩管道装置层流热边界层理论及其应用。对于速度边界层提出了相似性解的解析结果,给出了速度分布、边界层厚度、摩擦阻力和水头损失的解析计算表达式。对于温度边界层利用管道热边界层方程,推出了温度分布、温度边界层厚度和热流量的计算关系式,并给出了设计应用实例。     

不同初始条件下乙醇-空气预混合气层流燃烧火焰结构分析

给出了一个扩展的乙醇化学反应动力学机理并给予了验证。利用此扩展机理分别计算了不同初始条件下乙醇-空气混合气一维层流自由传播火焰中反应物、自由基、碳基中间产物和燃烧产物的分布规律,预测了NOx的浓度分布曲线。对于乙醇-空气火焰,得到的主要结论有：主要自由基OH、H和O浓度随初始压力增加而减小;随初始温度增加而增加;随氮气稀释度的增加而减小。自由基浓度随初始条件的变化规律部分地解释了实验和计算得到的层流燃烧速度随初始条件的变化规律。     

微细尺度下液体乙醇层流扩散火焰的特性分析

采用Fluent 6.3软件对微细尺度下液体乙醇层流扩散燃烧过程进行了数值模拟,同时借用实验方法对其可靠性进行了验证.结果表明:实验获得的火焰结构与数值模拟温度图高温区结构相似,而且火焰结构尺寸比数值模拟要低,数值模拟值与实验计算值吻合良好;H/d与Re呈线性增加,有外加电场的斜率较无电场大,正向电场的H/d比反向电场...     

不同羽流模型在封闭空间池火灾中的应用

利用不同羽流模型对封闭空间火灾进行建模,在结合实验测出的热释放速率基础上,计算了不同羽流模型下的烟气填充时间和温度变化情况。将计算结果和实验数据进行了对比,分析了不同羽流模型的适用性。结果表明:火灾初期,4种羽流模型下的烟气填充速度相近,其中McCaffrey羽流模型与实际烟气填充过程最为接近;火灾后期,Zukoski羽流模型最接近实际烟气填充过程;火灾过程中,Thomas羽流模型和Zukoski模型计算结果非常接近,Thomas羽流模型更适用于一般的工程计算;4种羽流模型下的烟气层温度和实验结果有很大差异,实际工程中均不建议用来预测烟气温度。     

管道热边界层理论的研究

研究了高粘性液体管道流动的热边界层理论。利用圆柱坐标粘性流运动基本微分方程,提出了管道热边界层方程,推导出边界层中的温度分布以及层流和紊流时热边界层厚度的常微分方程和解析解计算表达式,并通过Matlab编程实例,给出了热边界层厚度解析解与数值解的比较。计算结果表明:1)粘性的影响将使得热边界层的发展加快,随着粘性和流量的增大,其影响将更加显著;2)紊流时热边界层的发展比层流时要慢。     

层流条件下传质过程对舰船电场的影响

为了使直流电流元模型仿真结果更加接近实际情况,首先建立了螺旋桨圆盘等效模型;然后,结合电化学及流体力学相关理论,从流动腐蚀角度对舰船在海水中的腐蚀电流密度进行分析,并基于Navier-Stokes方程得出了圆盘表面氧气的传质过程控制下的极限腐蚀电流强度,建立了腐蚀电流元模型求解三层介质中的静电场;最后,进行了实验验证。结果表明:螺旋桨转速的增加会导致静电场幅值增加,且电场幅值的变化与测量点及船壳破损的位置有关,实际腐蚀过程中边缘效应的影响不可忽略。     

管流速度边界层解析

采用动量积分方法推出了管道流动中的速度边界层方程,给出了管道层流和紊流时速度边界层和核心区中的速度分布、边界层厚度的解析结果,并与冯·卡门动量积分方程推出的结果进行了比较.得到了管道层流和紊流时速度边界层入口段长度的表达式,表明比现有教材中所给出的公式数值要小.证明了管流中速度边界层的发展要远远快于热边界层.因此在研究管道热边界层流动时假设速度边界层已充分发展是合理的.     

二维水翼空化流动的数值模拟

基于RANS方程,结合不同湍流模型与空化模型对粘性流中二维NACA66012模型水翼附近流场进行数值计算与模拟.计算得到固定攻角、固定来流速度时升力系数和阻力系数随空化数的变化规律以及固定空化数时升力系数随攻角的变化规律,并对相应流场进行分析.在二维水翼空化流动的准稳态模拟中,重点对比分析了不同湍流模型、空化模型对空化流动模拟结果的影响,并将计算结果与实验数据进行比较.研究结果表明,在二维水翼附近空化流动的数值模拟中,采用k-ω湍流模型和均相流空化模型计算得到的结果与实验数据吻合较好.最后,采用分离涡模型对不稳定的空化流动进行了瞬态模拟,并得到空化流动的变化规律.     

管道热边界层减阻理论的应用研究

全面研究了高粘性液体管道流动的热边界层减阻理论的应用。利用管道热边界层理论中关于边界层的温度分布及层流、紊流时热边界层厚度的计算表达式,推证了管壁热流量及定性温度的计算表达式,利用指数型的粘温特性方程,采用积分方法推出了管道热边界层流动中层流和紊流摩擦水头损失的计算公式,并给出了设计应用实例。计算结果表明,对于高粘液体短管输送,其流动一般均为边界层入口段,热边界层减阻的最佳范围大致是管长L≤5km,管径D≤200mm。     

Numerical simulation of base flow with hot base bleed for two jet models

In order to improve the benefits of base bleed in base flow field, the base flow with hot base bleed for two jet models is studied. Two-dimensional axisymmetric Navier–Stokes equations are computed by using a finite volume scheme. The base flow of a cylinder afterbody with base bleed is simulated. The simulation results are validated with the experimental data, and the experimental results are well reproduced. On this basis, the base flow fields with base bleed for a circular jet model and an annulus jet model are investigated by selecting the injection temperature from 830 K to 2200 K. The results show that the base pressure of the annular jet model is higher than that of the circular jet model with the changes of the injection parameter and the injection temperature. For the circular jet model, the hot gases are concentrated in the vicinity of the base. For the annular jet model, the bleed gases flow into the shear layer directly so that the hot gases are concentrated in the shear layer. The latter temperature distribution is better for the increase of base pressure.     

Characteristics structure analysis on debris cloud in the hypervelocity impact of disk projectile on thin plate

In this paper, the gauge points setting is introduced in the SPH simulation to analyze the debris cloud structure generated by the hypervelocity impact of disk projectile on thin plate. Compared with the experiments, more detailed information of the debris cloud structure can be classified from the numerical simulation. However, due to the solitary dispersion and overlap display of the particles in the SPH simulation, accurate comparison between numerical and experimental results is difficult to be performed. To track the velocity and spatial distribution of the particles in the debris cloud induced from disk and plate, gauge points are locally set in the single-layer profile in the SPH model. By analyzing the gauge points’ spatial coordinate and velocity, the location and velocity of characteristic points in the debris cloud are determined. The boundary of debris cloud is achieved, as well as the fragments distribution outside the main structure of debris cloud.     

Effect of change of sand properties on travel distance of ricocheted debris

The debris from exploded buildings can ricochet after colliding with the ground, thus increasing the debris travel distance and danger from any associated impacts or collisions. To reduce this danger, the travel distance of ricocheted debris must be accurately predicted. This study analyzed the change in the travel distance of ricocheted concrete debris relative to changes in the properties of a sand medium. Direct shear tests were conducted to measure the change in internal friction angle as a function of temperature and water content of the sand. Finite element analysis (FEA) was then applied to these variables to predict the speed and angle of the debris after ricochet. The FEA results were compared with results of low-speed ricochet experiments, which employed variable temperature and water content. The travel distance of the debris was calculated using MATLAB, via trajectory equations considering the drag coefficient. As the internal friction angle decreased, the shear stress decreased, leading to deeper penetration of the debris into the sand. As the loss of kinetic energy increased, the velocity and travel distance of the ricocheted debris decreased. Changes in the ricochet velocity and travel distance of the debris, according to changes in the internal friction angle, indicated that the debris was affected by the environment.     

水下航行器头部流噪声数值仿真与实验

选取头部线型,对航行器头部基于RNG k-ε湍流模型及FW-H声学模型进行流噪声模拟,然后对3种头部线型的航行器在不同速度下分别进行水洞实验。通过对比分析数值仿真与实验结果发现,航行器头部流噪声随着频率的增大而逐渐减小,随着速度的增大而增大。在相同速度下,与头部线型2、头部线型3相比,头部线型1流噪声较小,具有更好的降噪作用。所采用的计算方法可以比较准确地模拟航行器头部流噪声情况。     

A three-stage model for the perforation of finite metallic plates by long rods at high velocities

A three-stage theoretical model is presented herein to predict the perforation of a thick metallic plate struck normally by a long rod at high velocities. The model is suggested on the basis of the assumption that the perforation of a thick metallic plate by a long rod can be divided into three stages: (1) initial penetration; (2) plug formation and (3) plug slipping and separation. Various analytical equations are derived which can be employed to predict the ballistic limit, residual velocity and residual length of the long rod. It is demonstrated that the present model predictions are in good agreement with available experimental results for the perforation of finite steel targets struck normally by steel as well as tungsten alloy long rods at high velocities. It is also demonstrated that the dynamic maximum shear stress of a plate material has strong effect on plug formation and plug thickness which, in turn, exerts considerable influence on the residual velocities and lengths of a long rod at impact velocities just above the ballistic limit.     

Simulation of natural fragmentation of rings cut from warheads

Natural fragmentation of warheads that detonates causes the casing of the warhead to split into various sized fragments through shear or radial fractures depending on the toughness,density,and grain size of the material.The best known formula for the prediction of the size distribution is the Mott formulae,which is further examined by Grady and Kipp by investigating more carefully the statistical most random way of portioning a given area into a number of entities.We examine the fragmentation behavior of radially expanding steel rings cut from a 25 mm warhead by using an in house smooth particle hydrodynamic(SPH) simulation code called REGULUS.Experimental results were compared with numerical results applying varying particle size and stochastic fracture strain.The numerically obtained number of fragments was consistent with experimental results.Increasing expansion velocity of the rings increases the number of fragments.Statistical variation of the material parameters influences the fragment characteristics,especially for low expansion velocities.A least square regression fit to the cumulative number of fragments by applying a generalized Mott distribution shows that the shape parameter is around 4 for the rings,which is in contrast to the Mott distribution with a shape parameter of 1/2.For initially polar distributed particles,we see signs of a bimodal cumulative fragment distribution.Adding statistical variation in material parameters of the fracture model causes the velocity numerical solutions to become less sensitive to changes in resolution for Cartesian distributed particles.     

基于图像对比度最优的频率步进ISAR成像方法

在频率步进高分辨ISAR成像中,目标的径向运动会带来距离多普勒耦合,从而对ISAR图像有较大的影响。提出了一种基于图像对比度最优的运动参数估计方法。该法分析了径向速度和径向加速度对多普勒像对比度函数的影响。通过构造相位补偿因子,在多普勒像中基于多普勒像对比度最优估计径向加速度。在径向加速度补偿后,在距离像中基于距离像对比度最优估计径向速度。进行运动补偿,利用RD算法实现了目标的高分辨ISAR成像。该方法具有运动参数估计精度高和计算量小的优点。仿真结果验证了方法的有效性。     

脉冲防暴水炮非淹没气体射流的RANS和LES模拟

为提高脉冲防暴水炮刺激剂的雾化水平,必须提高射流的出口速度和改善雾化带形状,而这些因素与管内非淹没气体射流的湍流流场息息相关。为准确描述湍流分布和水柱加速过程,对脉冲防暴水炮的非淹没气体射流进行了RANS和LES模拟。结果表示LES模型较RANS的标准k-ε模型能更为精确地描述湍流分布和管内非淹没气体射流速度的各向异性。但两者对于水柱加速过程的描述基本一致,只是由于LES模型的气液参混较为充分,气液速度相差较小,而可能导致两模型气体在喷口膨胀规律的异同。LES模型气液界面复杂,是用于研究管内气液流型的理想方法。该方法为三维模拟打下了较好的基础,所得结果可以作为管外射流研究的初始条件。     

FY-2型发动机燃烧室计算模型

本文提出了一个液体火箭发动机双组元自燃推进剂高压燃烧过程的计算模型。模型考虑了偏二甲肼的分解反应、四氧化二氮的离解反应、高压蒸发、液滴二次雾化以及燃烧室横截面上混合比和流强分布的不均匀性。应用该模型对FY-2型发动机的三种喷注器结构的燃烧效率及能量释放分布进行了理论计算,计算结果与试车数据和现象相当吻合。