A numerical study of turbulent flow over a two‐dimensional hill

Calculations of mean velocities and Reynolds stresses are reported for the recirculating flow established in the wake of two‐dimensional polynomial‐shaped obstacles that are symmetrical about a vertical axis and mounted in the water channel downstream of a fully developed channel flow for Re=6×10⁴. The study involves calculations of mean and fluctuating flow properties in the streamwise and spanwise directions and include comparisons with experimental data [Almeida GP, Durão DFG, Heitor MV. Wake flows behind two‐dimensional model hills. Experimental Thermal and Fluid Science 1993; 7: 87–101] for flow around a single obstacle with data resulting from the interaction of consecutive obstacles, using two versions of the low‐Reynolds number differential second‐moment (DSM) closure model. The results include analysis of the turbulent stresses in local flow co‐ordinates and reveal flow structure qualitatively similar to that found in other turbulent flows with a reattachment zone. It is found that the standard isotropization of production model (IPM), based on that proposed by Gibson and Launder [Ground effects on pressure fluctuations in the atmospheric boundary layer. Journal of Fluid Mechanics 1978; 86(3): 191–511], with the incorporation of the wall reflection model of Craft and Launder [New wall‐reflection model applied to the turbulent impinging jet. AIAA Journal 1992; 32(12): 2970–2972] predicts the mean velocities quite well, but underestimates the size of the recirculation region and turbulent quantities in the shear layer. These inadequacies are circumvented by adopting a new cubic Reynolds stress closure scheme based on that more recently developed by Craft and Launder [A Reynolds stress closure designed for complex geometries. International Journal of Heat and Fluid Flow 1996; 17: 245–254] which satisfies the two component limit (TCL) of turbulence. In this model the geometry‐specific quantities, such as the wall‐normal vector or wall distance, are replaced by invariant dimensionless gradient indicators. Also, the model captures the diverse behaviour of the different components of the stress dissipation, ε_ij, near the wall and uses a novel decomposition for the fluctuating pressure terms. Copyright © 2001 John Wiley & Sons, Ltd.     

低雷诺数下钝体三维尾迹中的涡量符号律

钝体是目前各种工程中广泛应用的一种结构.钝体绕流的尾迹涡动力学也是经典的流体力学研究对象之一.本文通过直接数值模拟,针对低雷诺数下各种钝体结构的不可压缩绕流,当形成三维尾迹时,研究具有特定符号的涡量分布特征.通过分析两类钝体结构,基本的直柱体和受到几何扰动的柱体,总结并得到了更为广泛适用的涡量符号律.通过对比并分析这两类钝体结构,结合理论证明的结果,进一步厘清了对产生涡量符号律的这两类钝体结构之间的内在物理关联,即引起自然失稳的小扰动在惯性力作用下产生的表面涡量只能向下游演化发展,而几何扰动则根据扰动位置,产生的表面涡量可以向扰动上游或下游演化发展.从而可以推测所有钝体结构尾迹中的各种型式的涡脱落模态,从涡量符号律的演化角度来看,实际上是一致的,都是起源于壁面产生特定符号组合规律的∏型涡.     

船舶尾流散射光信号及一维离散小波分析

用自行设计的测试系统测量了不同航速下船舶尾流的散射光信号,并选用一维离散小波Dmeyer小波对散射光信号进行了5层小波分析.测量和分析结果表明,随着航速增大,船舶尾流散射光照度减小,尾流气泡幕逐渐增强,气泡幕中气泡密度、气泡运动规律、不同直径气泡分布均随之变化.气泡幕的增强可能存在饱和度,在航速增大到一定值时,气泡幕会达到一稳定的密度分布.从小波分析得到的第五层逼近信号来看,不同航速下主峰位置、主峰个数以及峰值差均不同,不同航速下散射光细节信号的第一层均具有一定周期性,航速10 km/h时表现出完美的周期性,出现类似于同方向不同频率简谐振动叠加而出现“拍”的现象.     

Three-dimensional wake potential in a streaming dusty plasma

The oscillatory wake potential for a slowly moving or static test dust particulate in a finite temperature, collisionless and unmagnetized dusty plasma with a continuous flow of ions and dust particles has been studied. The collective resonant interaction of the moving test particle with the low-frequency and low-phase-velocity dust-acoustic mode is the origin of the periodic attractive force between the like polarity particulates along and perpendicular to the streaming ions and dust grains resulting into dust-Coulomb crystal formation. This wake potential can explain the three-dimensional dust-Coulomb crystal formation in the laboratory conditions.     

Investigations of wake flows of a flat plate in steady,oscillatory and combined flows

Numerical study on near wake flows of a flat plate in three kinds of oncoming flows is made by using the discrete vortex model and improved vorticity creation method. For steady oncoming flow, both gross and detailed features of the wake flow are calculated and discussed. Then, in harmonic oscillatory oncoming flow two different wake flow patterns withK _c=2,4 and 10 are obtained respectively. Our results present a new wake flow pattern for lowKc numbers (Kc<5) describing vortex shedding, pairing and moving in a period of the oscillatory flow starting from rest. The calculated drag and inertia force coefficients are closer to experimental data from the U-tube than the previous results of vortex simulation. For in-line combined oncoming flow the vortex lock-in and dynamic characteristics are simulated. The results are shown to be in good agreement with experiments. The project supported by National Natural Science Fundation of China and LNM of Institute of Mechanics. CAS     

轴向间隙对压气机时序效应影响之二：截面特性

本文实验研究不同轴向间隙、不同静叶时序角度对某低速轴流压气机出口流场的影响.结果表明,当一级静叶尾迹位于二级静叶流道中央位置时对应压气机最低效率状态;一级静叶尾迹重合或接近于二级静叶尾迹时对应压气机最高效率状态.随着轴向间隙的减小,压气机的扩压能力逐渐增强,通流能力下降.此外,设计工况下压气机输入功率也随轴向间隙的减小而增大.综合考虑轴向间隙对压气机扩压能力、通流能力及输入功率的影响,推测存在一个最佳轴向间隙,使得各项因素达到最优匹配,实现压气机的最佳性能.     

Sound speed in bubble film of ship wakes

As is distinct from general gas-liquid two-phase flow, a large number of bubbles with different diameters belong to ship wakes. Feasibility of Laplace equation, used to calculate wake sound speed (WSS), is confirmed based on differential postulation. Defect for calculating the adiabatic sound speed of gases in references is showed, and a concept of WSS is proposed clearly. A minimum WSS of 24.5 m/s is got when bubble ratio reads 0.5 according to the calculation when bubble dimension is less than that of resonance. Also a weak dependence of WSS on pressures is predicted. WSS from calculation corresponds with the experimental data of references well in high frequency domain, when the actual scale of bubbles is greater than the resonant scale. Supported by the National Natural Science Foundation of China (Grant No.10274046) and Pre-study Fund of Military Equipment (Grant No. 51448030101ZK1801)     

Axial electric wake field inside the induction gap exited by the intense electron beam

While an intense electron beam passes through the accelerating gaps of a linear induction accelerator,a strong wake field will be excited.In this paper a relatively simple model is established based on the interaction between the transverse magnetic wake field and the electron beam,and the numerical calculation in succession generates a magnetic wake field distribution along the accelerator and along the beam pulse as well.The axial electric wake field is derived based on the relation between field components of a resonant mode.According to some principles in existence,the influence of this field on the high voltage properties of the induction gap is analyzed.The Dragon-I accelerator is taken as an example,and its maximum electric wake field is about 17 kV/cm,which means the effect of the wake field is noticeable.     

PIV analysis of flow around a container ship model with a rotating propeller

The flow characteristics of the propeller wake behind a container ship model with a rotating propeller were investigated using a two-frame PIV (Particle Image Velocimetry) technique. Ensemble-averaged mean velocity fields were measured at four different blade phases and ensemble-averaged to investigate the flow structure in the near-wake region. The mean velocity fields in longitudinal planes show that a velocity deficit is formed in the regions near the blade tips and hub. As the flow develops in the downstream direction, the trailing vortices formed behind the propeller hub move upward slightly due to the presence of the hull wake and free surface. Interaction between the bilge vortices and the incoming flow around the hull causes the flow structure to be asymmetric. Contour plots of the vorticity give information on the radial distribution of the loading on the blades. The radial velocity profiles fluctuate to a greater extent under the heavy (J=0.59) and light loading (J=0.88) conditions than under the design loading condition (J=0.72). The turbulence intensity has large values around the tip and trailing vortices. As the wake develops in the downstream direction, the strength of the vorticity diminishes and the turbulence intensity increases due to turbulent diffusion and active mixing between the tip vortices and the adjacent wake flow.     

Numerical investigation of the effect of winglets on the evolution of an aircraft vortex wake

The effect of winglets on the aerodynamic characteristics of a heavy aircraft and the parameters of the vortex wake behind it is investigated for the landing regime. The solution of the complete problem is obtained by breaking up the wake into three regions, namely, the near, intermediate, and far flowfields, in which the corresponding subproblems are successively solved. The wake flowfields are obtained at different distances from the aircraft, together with the distributions of the mean azimuthal velocity over the vortex radius, and the lifetime of the vortex system is estimated for several one-and two-element wingtip versions. All the results are compared with those for the baseline layout with no winglets.