UNSTEADY/STEADY NUMERICAL SIMULATION OF THREE-DIMENSIONAL INCOMPRESSIBLE NAVIER-STOKES EQUATIONS ON ARTIFICIAL COMPRESSIBILITY

A mixed algorithm of central and upwind difference scheme for the solution of steady/unsteady incompressible Navier-Stokes equations is presented. The algorithm is based on the method of artificial compressibility and uses a third-order flux-difference splitting technique for the convective terms and the second-order central difference for the viscous terms. The numerical flux of semi-discrete equations is computed by using the Roe approximation. Time accuracy is obtained in the numerical solutions by subiterating the equations in pseudotime for each physical time step. The algebraic turbulence model of Baldwin-Lomax is ulsed in this work. As examples, the solutions of flow through two dimensional flat, airfoil, prolate spheroid and cerebral aneurysm are computed and the results are compared with experimental data. The results show that the coefficient of pressure and skin friction are agreement with experimental data, the largest discrepancy occur in the separation region where the lagebraic turbulence model of Baldwin-Lomax could not exactly predict the flow.

Dynamic flight stability of hovering model insects:theory versus simulation using equations of motion coupled with Navier-Stokes equations

In the present paper, the longitudinal dynamic flight stability properties of two model insects are predicted by an approximate theory and computed by numerical sim- ulation. The theory is based on the averaged model （which assumes that the frequency of wingbeat is sufficiently higher than that of the body motion, so that the flapping wings＇ degrees of freedom relative to the body can be dropped and the wings can be replaced by wingbeat-cycle-average forces and moments）; the simulation solves the complete equations of motion coupled with the Navier-Stokes equations. Comparison between the theory and the simulation provides a test to the validity of the assumptions in the theory. One of the insects is a model dronefly which has relatively high wingbeat frequency （164 Hz） and the other is a model hawkmoth which has relatively low wingbeat frequency （26 Hz）. The results show that the averaged model is valid for the hawkmoth as well as for the dronefly. Since the wingbeat frequency of the hawkmoth is relatively low （the characteristic times of the natural modes of motion of the body divided by wingbeat period are relatively large） compared with many other insects, that the theory based on the averaged model is valid for the hawkmoth means that it could be valid for many insects.

Navier-Stokes方程最优控制问题的一种新型投影稳定化方法

本文研究了高雷诺数下二维非定常Navier-Stokes方程最优控制问题的一种新型投影稳定化方法.通过L^2投影稳定化技巧,本文绕开了inf-sup条件对等阶有限元的束缚,克服了雷诺数较大时,对流占优引起的振荡.该方法的优点在于:所有计算只需要在同一套网格上执行,不需要嵌套网格或者将速度和压力的梯度投影到粗网格上.

非定常Navier-Stokes方程的一种非线性局部投影稳定化有限元方法

针对非定常Navier-Stokes方程,本文提出了一种基于非线性对流项和压力梯度的局部投影稳定化有限元方法.该方法在空间上采用等阶有限元,时间上采用隐式有限差分.本文建立了非定常Navier-Stokes方程的全离散数值格式,进而分析了离散解的稳定性和收敛性.值得注意的是,该方法中得到的误差估计随着流体雷诺数的增大依然有效.

基于局部时均Navier-Stokes模型的分域计算方法

基于标准局部时均Navier-Stokes模型中控制参数fk的取值特点,提出一种基于分域思想的计算方法。针对不同的流域采用不同的f_(k)值,实现在同一个计算流域设置不同湍流模型的效果。应用该方法分别计算绕方柱的单相流动和绕Clark-y水翼的非定常空化流动,并将计算结果与相应实验结果进行对比。结果表明:数值计算得到的方柱表面压力系数分布以及流场中不同截面处的速度分布均与实验结果吻合较好;新方法可以很好地捕捉到Clark-y水翼吸力面空穴形态随时间的演化过程,以及水翼升力系数随时间的波动规律。

Study of Tunnel Thruster Performance and Flow by Quasi-Steady Reynolds-Averaged Navier-Stokes Simulation

A numerical approach based on the solution of the Reynolds-averaged Navier-Stokes(RANS) equations using the shear-stress transport(SST) turbulence model has been employed to investigate the hydrodynamic performance and flow of tunnel thrusters.The flow passages between adjacent blades are discretized with prismatic cells so that the boundary layer flow is resolved down to the viscous sub-layer.The hydrodynamic performances predicted by the quasi-steady approach agree well with the experimental data for three impellers covering a range of blade area and pitch.Through analysis of the flow field,the reason why the hub of impeller also contributes to thrust which can amount to 40%—60% of the impeller thrust,and the mechanism of the impeller inducing an axial force on the hull are elucidated.

一种半潜式商用6 MW级风力机载荷数值模拟研究

针对海上漂浮式风力机在其运行状态下的叶轮气动载荷与平台运动状态难以预测的问题,本文以一种商用6 MW级漂浮式风力机为研究对象,基于非稳态的雷诺平均湍流模型,进行了全耦合数值模拟和水池模型试验研究。结果显示:浮式风力机自由衰减周期的模拟值在纵摇、横揺和垂荡上与实验值吻合度较高,而在纵荡、横荡和艏摇上,衰减周期的模拟值与实验值存在一定误差,这主要是由数值模型中对系泊系统进行悬链线简化时造成的。在静水工况下,风力机气动载荷的波动主要受塔影效应影响,机舱加速度的波动与叶轮推力系数变化呈正相关,浮式风力机纵荡和纵摇运动主要受叶轮气动载荷波动的影响;在规则波和非规则波工况下,叶轮推力的波动受浮式基础纵荡和纵摇的影响较大,叶轮推力系数变化和机舱速度呈负相关。浮式风力机的运动主要受波浪载荷的影响,气动载荷对其影响相对较小。

不同叶高水平的透平叶片气动特性分析

为了能够通过CFD手段优化透平叶片气动性能,本文使用雷诺平均方法针对工程上应用的66、44以及22 mm共3种典型叶高水平的透平模型进行了数值模拟,并将计算结果同实验测量结果进行了对比。同时,使用大涡模拟数值方法对22 mm叶高的模型进行非定常计算,得到了与实验结果吻合更好的等熵效率、质量流量等流场宏观参数,在三维流场上透平叶片的叶根与叶顶处的流动更为复杂。研究结果表明:雷诺平均方法可以对66和44 mm叶高的透平模型进行较准确的评估,对于22 mm叶高的透平,只有大涡模拟方法才能够清晰地捕捉到端壁区域紊乱的流动细节。叶片端部区域损失较大,雷诺平均方法处理得到的短叶片端壁区域丢失了流动的脉动细节,导致无法进行准确计算其端壁区域的流动。

水陆两栖飞机全机模型静水滑行水动性能预报

水面起飞性能是水面飞行器的基本性能,也是总体技术的核心,涉及多个学科领域。水陆两栖飞机水面高速滑行水动力性能与排水型船不同,具有速度高、运动复杂等特点,高速滑行时一方面受到较大的水动升力,另一方面受到机翼的升力。结合水陆两栖飞机水面高速滑行特点,利用雷诺平均法(Reynolds average navier-stokes, RANS)数值方法和重叠网格技术对水陆两栖飞机全机模型开展数值仿真模拟,分析了自由液面水气分布、机身底部压力分布特征,并将阻力、姿态和升沉与水池模型试验结果进行对比,验证了数值方法的准确性,为水陆两栖飞机静水滑行水动性能数值预报提供技术基础。

Investigating the Effects of Injection Pipe Orientation on Mixing and Heat Transfer for Fluid Flow Downstream a T-Junction

At T-junctions, where hot and cold streams flowing in pipes join and mix, significant temperature fluctuations can be created in very close neighborhood of the pipe walls. The wall temperature fluctuations cause cyclical thermal stresses which may induce fatigue cracking. Temperature fluctuation is of crucial importance in many engineering applications and especially in nuclear power plants. This is because the phenomenon leads to thermal fatigue and might subsequently result in failure of structural material. Therefore, the effects of temperature fluctuation in piping structure at mixing junctions in nuclear power systems cannot be neglected. In nuclear power plant, piping structure is exposed to unavoidable temperature differences in a bid to maintain plant operational capacity. Tightly coupled to temperature fluctuation is flow turbulence, which has attracted extensive attention and has been investigated worldwide since several decades. The focus of this study is to investigate the effects of injection pipe orientation on flow mixing and temperature fluctuation for fluid flow downstream a T-junction. Computational fluid dynamics (CFD) approach was applied using STAR CCM+ code. Four inclination angles including 0 (90), 15, 30 and 45 degrees were studied and the mixing intensity and effective mixing zone were investigated. K-omega SST turbulence model was adopted for the simulations. Results of the analysis suggest that, effective mixing of cold and hot fluid which leads to reduced and uniform temperature field at the pipe wall boundary, is achieved at 0 (90) degree inclination of the branch pipe and hence may lower thermal stress levels in the structural material of the pipe. Turbulence mixing, pressure drop and velocity distribution were also found to be more appreciable at 0 (90) degree inclination angle of the branch pipe relative to the other orientations studied.

Numerical Simulation on Hydraulic Performances of Quarter Circular Breakwater

Quarter circular breakwater （QCB） is a new-type breakwater developed from senti-circular breakwater （SCB）. The superstructure of QCB is composed of a quarter circular front wall, a horizontal base slab and a vertical rear wall. The width of QCB＇ s base slab is about half that of SCB, which makes QCB suitable to be used on relatively finn soil foundation. The numerical wave flume based on the Reynolds averaged Navier-Stokes equations for impressible viscosity fluid is adopted in this paper to simulate the hydraulic performances of QCB. Since the geometry of both breakwaters is similar and SCB has been studied in depth, the hydraulic performances of QCB are given in comparison with those of SCB.

Delayed detached eddy simulations of fighter aircraft at high angle of attack

The massively separated flows over a realistic aircraft configuration at 40？, 50？, and 60？angles of attack are studied using the delayed detached eddy simulation（DDES）.The calculations are carried out at experimental conditions corresponding to a mean aerodynamic chord-based Reynolds number of 8.93 × 10~5 and Mach number of 0.088. The influence of the grid size is investigated using two grids, 20.0×10~6cells and 31.0 × 10~6 cells. At the selected conditions, the lift,drag, and pitching moment from DDES predictions agree with the experimental data better than that from the Reynoldsaveraged Navier–Stokes. The effect of angle of attack on the flow structure over the general aircraft is also studied, and it is found that the dominated frequency associated with the vortex shedding process decreases with increasing angle of attack.

Lateral dynamic flight stability of hovering insects: theory vs. numerical simulation

In the present paper, the lateral dynamic flight stability properties of two hovering model insects are predicted by an approximate theory based on the averaged model, and computed by numerical simulation that solves the complete equations of motion coupled with the Naviertokes equations. Comparison between the theoretical and simulational results provides a test to the validity of the assumptions made in the theory. One of the insects is a model dronefly which has relatively high wingbeat frequency （164Hz） and the other is a model hawkmoth which has relatively low wingbeat frequency （26 Hz）. The following conclusion has been drawn. The theory based on the averaged model works well for the lateral motion of the dronefly. For the hawkmoth, relatively large quantitative differences exist between theory and simulation. This is because the lateral non-dimensional eigenvalues of the hawkmoth are not very small compared with the non-dimensional flapping frequency （the largest lateral non-dimensional eigenvalue is only about 10% smaller than the non-dimensional flapping frequency）. Nevertheless, the theory can still correctly predict variational trends of the dynamic properties of the hawkmoth＇s lateral motion.

基于RANS和LES的高大空间建筑气流组织仿真和热舒适度评价方法

针对大空间建筑的暖通空调设计,开展气流组织分析和热舒适评价对于改善室内环境热舒适度和降低能耗具有重要意义。结合基于雷诺时均方程的稳态分析和基于大涡模拟的瞬态分析这2种计算流体力学分析方法的特点,建立了高大空间建筑气流组织仿真方案和热舒适度评价方法。利用稳态分析计算消耗较小的特点,开展多工况热舒适度和空气质量评价;选取典型工况实施计算消耗较大的瞬态分析,获取空气调节全过程,给出室内温度达到设定温度所需要的空调运行时间,从而优化空调运行策略,降低能耗。基于实验结果对2种方法的准确性进行了验证,介绍了所用方法在实际工程项目中的应用,供其他工程参考。

斜流中船后螺旋桨水动力载荷实尺度计算分析

斜流条件下螺旋桨可能受到较大的侧向载荷,会严重影响船舶推进效率和尾轴的安全。本文采用RANS(Reynolds-Averaged Navier Stokes)方法,结合SST k-ω两方程湍流模型和滑动网格方法,对国际标模KCS斜流中船后螺旋桨水动力载荷进行实尺度数值计算,分析不同漂角时螺旋桨在纵向、横向、垂向3个方向上的力和力矩的变化规律。计算考虑±20°,±15°,±10°,±5°以及0°漂角,结果表明斜流对螺旋桨推进载荷和侧向载荷都有较大影响,且相对漂角具有不对称特点。通过单独桨叶的推力变化曲线分析漂角对不同相位角度处螺旋桨载荷的影响规律,结果显示在桨盘面下端附近桨叶载荷更为敏感于漂角变化。通过与其他文献数据对比,分析斜流下螺旋桨载荷的尺度效应,结果表明轴向载荷和垂向载荷系数的尺度效应较大。

贝宁海滩上波浪传播演变特性研究

为分析贝宁海滩上波浪传播演变特性,基于开源波浪数值计算软件COBRAS建立了贝宁典型海滩剖面数值模型,模型中采用k-epsilon紊流模型求解雷诺应力,采用流体体积法捕捉自由液面,并采用斜坡上波浪破碎试验结果对数值模型进行了验证。基于该模型对常浪条件和极端波浪条件下海滩上波浪传播规律的模拟结果表明:常浪条件下波浪主要在沙坝附近发生破碎,极端波浪条件下波浪在沙坝外侧200 m处开始发生破碎;破碎区域内水质点速度较大,常浪条件下沙坝周围的流速可达7.5 m/s,极端波浪条件下破波带内水质点速度可达12.4 m/s,且波浪回流与入射波浪在沙坝周围相互作用会形成较强的涡旋;随着波浪非线性的增强,波浪爬高也逐渐增大,在极端波浪条件下,沙丘上会发生越浪。

下表面射流的超临界翼型气动性能分析

为探究下表面射流关键参数对超临界翼型气动性能的影响,采用雷诺平均Navier-Stokes(RANS)方程与Spalart-Allmaras(S-A)湍流模型进行数值模拟。通过比较基准RAE2822翼型与下表面射流翼型的流场,验证下表面射流能够在翼型后缘诱导产生逆时针分离涡,带动流线向下偏折,增加了翼型的等效弯度,同时加大前缘的吸力峰,从而提高翼型的气动性能。进一步探究射流位置、射流动量系数、射流角度、马赫数等关键参数对RAE2822翼型气动性能的影响规律。结果表明:给定状态下,下表面射流的位置越靠后,动量系数越大,翼型的气动性能越优。下表面射流在α=0°和2°时的最优射流角度为110°,在α=4°时的最优射流角度为160°,且在最优射流角度下能有效提高翼型马赫数在0.3~0.6范围内的气动性能。

基于OpenFOAM的螺旋桨紧急倒车工况数值模拟

螺旋桨在紧急倒车工况下的水动力特性与船舶的紧急制动能力密切相关并直接影响船舶的航行安全性.基于开源计算流体动力学平台OpenFOAM中的雷诺平均求解器对螺旋桨在紧急倒车工况下的水动力特性及绕流场开展数值研究.以5叶螺旋桨DTMB4381模型为研究对象,对其正车前进以及紧急倒车工况进行数值模拟.通过与国际上公开的模型试验结果进行对比,验证了所采用的数值方法在预报螺旋桨不同工况下水动力性能方面的有效性.基于数值模拟获得的水动力载荷及流场信息,探讨了紧急倒车工况下局部绕流场特征随进速变化的规律及其与螺旋桨整体水动力特性之间的关系,为船舶紧急倒车制动能力评估提供了理论依据.

近海V形山谷地形输电线路的风场仿真与风灾事故分析

山地风场的复杂多变性是造成山区输电线路风灾事故频发的重要原因。本文采用CFD数值仿真技术对不同风向角下典型的近海V形山谷地形下的输电线路风场进行了仿真。基于雷诺时均模型(RANS)仿真方法比较了半径分别为3 km、5 km和8 km三种尺度地形下风场计算结果的差异。针对事故塔位的不利风向工况,进一步采用大涡模拟(LES)技术对风场进行了补充分析,并比较了其与RANS计算结果的差异。在此基础上,分析了线路发生跳线风偏放电事故的原因。研究结果表明V形山谷两侧山脉上不利的风速加速效应出现在山脊线的迎风前端,其在东、西两侧山脉的最大水平风速加速比可达1.23和1.65,而最大竖向风速比可达0.45和0.30。山腰位置处塔在背风向下可能受到显著的下沉气流作用。山谷中心位置处风速加速效应不明显且可能在某些风向下存在衰减。不同尺度地形仿真结果的比较表明,5 km半径的中尺度地形与大尺度地形仿真结果较为一致,而采用3 km小尺度地形可能会产生明显误差。LES模拟的平均风剖结果比对应的RANS结果略偏大。地形的影响会导致事故塔位处的水平极值风速相比来流极值风增大13%,同时产生相当于0.2倍来流风速的竖向风。仿真显示,在不利风向下事故塔位处存在明显的水平风速加速和竖向风速,从而造成跳线风偏事故的发生。

A FULL DISCRETE STABILIZED METHOD FOR THE OPTIMAL CONTROL OF THE UNSTEADY NAVIER-STOKES EQUATIONS

In this paper, a full discrete local projection stabilized （LPS） method is proposed to solve the optimal control problems of the unsteady Navier-Stokes equations with equal order elements. Convective effects and pressure are both stabilized by using the LPS method. A priori error estimates uniformly with respect to the Reynolds number are obtained, providing the true solutions are sufficient smooth. Numerical experiments are implemented to illustrate and confirm our theoretical analysis.