An Investigation into the Effects of the Reynolds Number on High-Speed Trains Using a Low Temperature Wind Tunnel Test Facility

A series of tests have been conducted using a Cryogenic Wind Tunnel to study the effect of Reynolds number(Re)on the aerodynamic force and surface pressure experienced by a high speed train.The test Reynolds number has been varied from 1 million to 10 million,which is the highest Reynolds number a wind tunnel has ever achieved for a train test.According to our results,the drag coefficient of the leading car decreases with higher Reynolds number for yaw angles up to 30º.The drag force coefficient drops about 0.06 when Re is raised from 1 million to 10 million.The side force is caused by the high pressure at the windward side and the low pressure generated by the vortex at the lee side.Both pressure distributions are not appreciably affected by Reynolds number changes at yaw angles up to 30°.The lift force coefficient increases with higher Re,though the change is small.At a yaw angle of zero the down force coefficient is reduced by a scale factor of about 0.03 when the Reynolds number is raised over the considered range.At higher yaw angles the lift force coefficient is reduced about 0.1.Similar to the side force coefficient,the rolling moment coefficient does not change much with Re.The magnitude of the pitching moment coefficient increases with higher Re.This indicates that the load on the front bogie is higher at higher Reynolds numbers.The yawing moment coefficient increases with Re.This effect is more evident at higher yaw angles.The yawing moment coefficient increases by about 6%when Re is raised from 1 million to 10 million.The influence of Re on the rolling moment coefficient around the leeward rail is relatively smaller.It increases by about 2%over the considered range of Re.

Effects of the Reynolds number on the mean skin friction decomposition in turbulent channel flows

As the Reynolds number increases, the skin friction has been identified as the dominant drag in many practical applications. In the present paper, the effects of the Reynolds number on the mean skin friction decomposition in turbulent channel flows up to Reτ= 5 200 are investigated based on two different methods, i.e., the FukagataIwamoto-Kasagi(FIK) identity(FUKAGATA, K., IWAMOTO, K., and KASAGI, N.Contribution of Reynolds stress distribution to the skin friction in wall-bounded flows.Physics of Fluids, 14(11), L73–L76(2002)) and the Renard-Deck(RD) identity(DECK,S., RENARD, N., LARAUFIE, R., and WEISS, P.′E. Large-scale contribution to mean wall shear stress in high-Reynolds-number flat-plate boundary layers up to Reθ= 13 650.Journal of Fluid Mechanics, 743, 202–248(2014)). The direct numerical simulation(DNS) data provided by Lee and Moser(LEE, M. and MOSER, R. D. Direct numerical simulation of turbulent channel flow up to Reτ≈ 5 200. Journal of Fluid Mechanics,774, 395–415(2015)) are used. For these two skin friction decomposition methods, their decomposed constituents are discussed and compared for different Reynolds numbers.The integrands of the decomposed constituents are locally analyzed across the boundary layer to assess the actions associated with the inhomogeneity and multi-scale nature of turbulent motion. The scaling of the decomposed constituents and their integrands are presented. In addition, the boundary layer is divided into three sub-regions to evaluate the contributive proportion of each sub-region with an increase in the Reynolds number.

Effects of the Reynolds number on a scale-similarity model of Lagrangian velocity correlations in isotropic turbulent flows

A scale-similarity model of a two-point two-time Lagrangian velocity correlation(LVC) was originally developed for the relative dispersion of tracer particles in isotropic turbulent flows(HE, G. W., JIN, G. D., and ZHAO, X. Scale-similarity model for Lagrangian velocity correlations in isotropic and stationary turbulence. Physical Review E, 80, 066313(2009)). The model can be expressed as a two-point Eulerian space correlation and the dispersion velocity V. The dispersion velocity denotes the rate at which one moving particle departs from another fixed particle. This paper numerically validates the robustness of the scale-similarity model at high Taylor micro-scale Reynolds numbers up to 373, which are much higher than the original values(R_λ = 66, 102). The effect of the Reynolds number on the dispersion velocity in the scale-similarity model is carefully investigated. The results show that the scale-similarity model is more accurate at higher Reynolds numbers because the two-point Lagrangian velocity correlations with different initial spatial separations collapse into a universal form compared with a combination of the initial separation and the temporal separation via the dispersion velocity.Moreover, the dispersion velocity V normalized by the Kolmogorov velocity V_η ≡ η/τ_η in which η and τ_η are the Kolmogorov space and time scales, respectively, scales with the Reynolds number R_λ as V/V_η ∝ R_λ^(1.39) obtained from the numerical data.

Experimental Investigation of Reynolds Number Effect on Wind Turbine Profiles in the Cryogenic Wind Tunnel Cologne DNW-KKK

Wind turbine size has increased continuously and correspondingly also its Reynolds numbers. The Reynolds number effect can therefore no longer be ignored in design and optimization of wind turbines. Reliable profile test data should be available. A suitable facility for testing wind turbine profiles at high Reynolds numbers is the Cryogenic Wind Tunnel Cologne DNW-KKK. By means of injecting liquid nitrogen the tunnel can be cooled down to 100 K and the Reynolds number therefore can be raised accordingly. The maximum Reynolds number for 2D profile tests can reach 27x10^6. In this paper the test uncertainty and the flow quality of DNW-KKK were analyzed. Then some test results on the Reynolds number effect of the wind turbine profiles will be presented. The Reynolds number effect is different from model to model. Especially for thick profiles and flow control devices the Reynolds number effect is not always like the description in literature.

尺度效应对低Reynolds数下微/小柱群通道内对流换热的影响

引言自20世纪90年代,随着超大规模集成电子及微电子机械系统（MEMS）的迅猛发展,其散热问题逐渐成为一个研究热点[1],而柱群结构是解决这一问题的重要方法之一。柱群能大幅增加换热结构的面体比,同时柱之间的相互扰动使流动发生转捩,从而能对高热通量场合进行有效冷却,

Periodical streaming potential and electro-viscous effects in microchannel flow

This paper presents an analytical solution to periodical streaming potential, flow-induced electric field and velocity of periodical pressure-driven flows in twodimensional uniform microchannel based on the Poisson-Boltzmann equations for electric double layer and Navier-Stokes equation for liquid flow. Dimensional analysis indicates that electric-viscous force depends on three factors： （1） Electric-viscous number representing a ratio between maximum of electric-viscous force and pressure gradient in a steady state, （2） profile function describing the distribution profile of electro-viscous force in channel section, and （3） coupling coefficient reflecting behavior of arnplitude damping and phase offset of electro-viscous force. Analytical results indicate that flow-induced electric field and flow velocity depend on frequency Reynolds number （Re = wh^2/v）. Flow-induced electric field varies very slowly with Re when Re 〈 1, and rapidly decreases when Re 〉 1. Electro-viscous effect on flow-induced electric field and flow velocity are very significant when the rate of the channel width to the thickness of electric double layer is small.

先进飞行器雷诺数效应若干研究进展及展望

雷诺数效应对先进飞行器气动特性预测至关重要,其影响着飞行器飞行性能、研制成本和安全。本文深入探讨了3个核心问题:首先,介绍了不同研究手段在探索雷诺数效应上的优势和局限,特别强调大型低温风洞是获取真实飞行雷诺数气动特性数据的有效途径;其次,详细分析了大飞机等先进飞行器在高雷诺数下呈现的复杂流动现象及其对气动特性的影响,如多段翼型的缝道流动、超临界翼型的激波/边界层干扰、飞行器的过失速机动特性以及飞翼布局飞行器的进气道性能等,并揭示了高雷诺数效应的非线性和复杂性;最后,探讨了修正雷诺数效应的方法,强调了融合风洞试验、数值计算和飞行试验数据的重要性,通过分析现有修正模型的适用范围和局限性,提出了发展更完善的修正模型和算法的建议。文章还对雷诺数效应的未来研究方向进行了研判和展望。

Numerical Study on Low-Reynolds Compressible Flows around Mars Helicopter Rotor Blade Airfoil

High-speed rotor rotation under the low-density condition creates a special low-Reynolds compressible flow around the rotor blade airfoil where the compressibility effect on the laminar separated shear layer occurs. However, the compressibility effect and shock wave generation associated with the increase in the Mach number (M) and the trend change due to their interference have not been clarified. The purpose is to clear the compressibility effect and its impact of shock wave generation on the flow field and aerodynamics. Therefore, we perform a two-dimensional unsteady calculation by Computational fluid dynamics (CFD) analysis using the CLF5605 airfoil used in the Mars helicopter Ingenuity, which succeeded in its first flight on Mars. The calculation conditions are set to the Reynolds number (Re) at 75% rotor span in hovering (Re = 15,400), and the Mach number was varied from incompressible (M = 0.2) to transonic (M = 1.2). The compressible fluid dynamics solver FaSTAR developed by the Japan aerospace exploration agency (JAXA) is used, and calculations are performed under multiple conditions in which the Mach number and angle of attack (α) are swept. The results show that a flow field is similar to that in the Earth’s atmosphere above M = 1.0, such as bow shock at the leading edge, whereas multiple λ-type shock waves are observed over the separated shear layer above α = 3° at M = 0.80. However, no significant difference is found in the Cp distribution around the airfoil between M = 0.6 and M = 0.8. From the results, it is found that multiple λ-type shock waves have no significant effect on the airfoil surface pressure distribution, the separated shear layer effect is dominant in the surface pressure change and aerodynamic characteristics.

桥梁风工程研究中的雷诺数效应研究进展

桥梁风工程研究中的雷诺数效应问题是伴随着风洞试验方法产生的一个基础性问题,随着桥梁尺寸的增大其雷诺数也逐渐增大,风洞试验雷诺数和实桥梁雷诺数的差别对试验结果的影响越来越受重视。该研究阐述了雷诺数效应问题的由来,回顾了雷诺数效应研究的发展历程,总结了针对圆形断面、矩形断面、主梁断面等不同桥梁结构断面雷诺数效应问题的研究进展,包括结构周围流场、气动力、风致振动随雷诺数的变化,指出了桥梁风工程雷诺数效应研究中尚待解决的问题,为今后该领域的研究提供参考和建议。

气井高速非达西效应主控因素分析

气藏开发实践表明,高速非达西效应对气井产能有着重要影响,不同的气藏,高速非达西效应的影响程度是不同的。对于地层压力较低的气藏,当气井产量较高时,高速非达西效应表现比较强;而对于地层压力较高的气藏,相同的气井产量,高速非达西效应可能并不强。其原因在于气体在较高的地层压力下压缩程度很强,密度、黏度更大,天然气的渗流速度更低,高速非达西效应更弱。根据气井产能方程和雷诺数方程,从气井产量、储层物性和气体性质等方面对影响非达西效应的主要因素进行了敏感性研究,基于临界雷诺数得到了达西和非达西渗流界限,建立了天然气达西渗流图版。通过该图版,可以明确非达西效应的强弱,进而为确定气井配产上限提供指导。

CHN-T2标模跨声速抖振特性及雷诺数效应研究

新一代客机具有较高的巡航速度,跨声速抖振和雷诺数效应研究是其气动设计中的关键一环。采用基于k-ωSST湍流模型耦合延迟脱体涡模拟技术的高精度数值模拟方法,针对CHN-T2宽体客机气动标模开展了相关研究,并基于非定常计算明确了CHN-T2标模在巡航马赫数Ma=0.85、飞行雷诺数Re=5×10^(7)工况下的抖振始发迎角约为4.4°。结果表明,CHN-T2标模机翼在抖振超临界迎角下同时存在由激波弦向振荡主导的低频成分(St=0.0297)和由翼根尾缘复杂高压区主导的高频成分(St=0.314)。在雷诺数效应方面,从风洞实验雷诺数(Re=5×10^(6))到飞行雷诺数(Re=5×10^(7))巡航状态下,CHN-T2机翼激波位置后移约10%当地弦长,附面层高度降低1/2~1/10,进而引发升/阻力系数发生明显变化。升力系数和摩阻系数的雷诺数效应不随迎角改变,而压阻系数的雷诺数效应与迎角线性相关。同时,雷诺数变化会显著影响抖振非定常流场求解,过低的模拟雷诺数会导致激波振荡消失。

REYNOLDS NUMBER EFFECTS IN TALL BUILDING WIND TUNNEL TESTS

In wind tunnel tests of tall building models comprised of rounded or streamlined surfaces, Reynolds Number Effects (RNE) may be remarkable. In most researches and projects, owing to the presence of sharp edged corners at model, RNE was often treated as negligible, and data colleCted in subcritical flow regime were applied directly to designs which were sure to be supercritical without any modification. But it was proved necessary to take RNE into consideration when a model had predominant rounded smooth surface(s). Some research activities were devoted to the mentioned condition and two experimental techniques accompanied by two wind tunnel model tests were introduced in the article. The authors also presented some amusing phenomenon such as extremely low pressure coefficients caused by the separating bubbles when now past sharp edged corners, unsymmetrical pressure coefficient distributions commenced by biased gap f'low (seen Figs. 3, 4) while models were placed symmetrically in the approaching flow.

基于标度律的壁湍流运动分解与雷诺数效应

壁湍流广泛存在于自然界和工程中,对其深入研究和理解有助于发展新的计算模型和调控手段。湍流具有多尺度性,壁面带来的各向异性使得壁湍流多尺度运动更为复杂。本文探讨和总结了基于标度律的壁湍流运动分解方法:内–外分解方法和外区分解方法,其中内–外分解方法基于内区湍流运动的雷诺数无关性,而外区分解方法基于Townsend的附着涡标度律;讨论了分解后壁湍流运动统计特性的雷诺数效应,给出了内区湍流运动达到雷诺数无关和出现外区湍流运动的2个临界雷诺数。

Effects of Reynolds number and Schmidt number on variable density mixing in shock bubble interaction

Effects of Reynolds(Re)number and Schmidt(Sc)number on the flow structures and variable density mixing are numerically investigated through the canonical shock cylindrical bubble interaction.By determining the viscosity and diffusivity within a wide range,the controlling parameters,total vortex circulation,and compression rate,are conservative under a broad range of Re and Sc numbers(Re≈10^(3)-10^(5)and Sc≈0.1-5)in the same shock Mach(Ma)number condition(Ma=2.4).As for the Re number effect,the circulation of secondary baroclinic vorticity(SBV),induced by the main vortex centripetal acceleration,is observed to be higher in high Re number and vice versa.Based on the vorticity transport equation decomposition,a growth-inhibition vorticity dynamics balance mechanism is revealed:the vorticity viscous term grows synchronously with baroclinic production to inhibit SBV production in low Re number.By contrast,the viscous term terminates the baroclinic term with a time lag in high Re number,leading to the SBV production.Since the SBV reflects the local stretching enhancement based on the advection-diffusion equation,mixing is influenced by the Sc number in a different behavior if different Re numbers are considered.The time-averaged variable density mixing rate emerges a scaling law with Sc number asχ^(∗)=β·Sc^(−α),where the coefficientβ∼Re−0.2 and the scaling exponentα∼Re−0.385.The understanding of Re number and Sc number effect on variable density mixing provides an opportunity for mixing enhancement from the perspective of designing the viscosity and diffusivity of the fluid mixture.

NUMERICAL SIMULATION OF REYNOLDS NUMBER EFFECT ON EFFETIVE WAKE FIELD AND HYDRODYNAMIC PERFORMANCE OF PROPELLER BEHIND SHIP

The Reynolds number effect of the interaction between the three-dimen-sional ship stern with multi-propellers and its corresponding hydrodynamic performance under four different orders of the Reynolds number (including the full scale Reynolds number 1. 67×109 and the model scale Reynolds number 1. 67×106) are numerically investigated in this paper. This approach to propeller-hull interaction is based on three-di-mensional unsteady RANS equations coupled with a propeller performance program in an interactive and iterative manner to predict the combined flow field and hydrodynamic per- formance of propeller. By comparing the computed effective wake distribution and fraction under four different orders of the Reynolds number, the scale effect of nominal and effec-tive wake distribution is examined and discussed.

球腔内低雷诺数流体中颗粒输运研究进展

受限环境下低雷诺数流体中的颗粒输运与生物、医药、化工和能源等应用密切相关.近年来,球腔内低雷诺数流体中的颗粒输运引起了广泛关注,它在细胞内生命活动和微流控封装技术中发挥着关键作用.为了掌握颗粒输运规律、揭示微观力学机理,各国学者进行了广泛的理论、数值和实验研究,取得了一系列成果.本文将梳理当前的研究进展,分别从理论模型、数值模拟和实验研究三方面,介绍关于球腔内低雷诺数流体中颗粒输运的重要工作.理论模型方面,主要工作包括刚性无滑移壁面、边界滑移和可变形壁面等情况下单个及多个颗粒输运的研究;数值模拟方面,重要工作包括模拟不同形状颗粒在静止与旋转球腔内的输运,研究颗粒的水动力迁移率与运动轨迹;实验研究方面,相关工作包含水液滴内颗粒三维轨迹、扩散系数的观测,以及利用球腔内颗粒布朗运动来计算受限环境性质的相关研究.通过总结相关成果,旨在为微纳尺度流动与颗粒输运领域的专家学者提供参考.

壁面约束下椭球颗粒曳力特性研究

颗粒两相流系统广泛存在于自然界和工程应用中,实际颗粒往往并非球形且受其附近壁面的影响。基于欧拉-拉格朗日方法的颗粒两相流数值模拟已成为非球形颗粒两相流系统设计的重要工具,然而其准确性受限于非球形颗粒曳力模型。因此,深入研究壁面约束下非球形颗粒曳力特性并发展近壁修正预测模型具有重要意义。本文采用直接数值模拟方法对有限雷诺数(0.5≤Re≤10)下,不同颗粒长轴取向与来流之间的夹角以及颗粒-壁面间距的单椭球颗粒曳力特性开展详细数值研究,分析比较不同工况下曳力系数的变化,探明雷诺数、攻角以及壁面间距对椭球颗粒曳力系数的影响规律,并评估现有自由流中椭球颗粒曳力关系式的适用性,最后发展了考虑近壁修正的椭球颗粒曳力预测模型,为优化非球形颗粒两相流数值模拟工具提供重要支撑。

超大型冷却塔风荷载特性风洞试验研究

对某超大型冷却塔进行同步测压风洞试验获得内、外表面的脉动风压分布。在外压测试中,改变外表面粗糙度和调整风速等措施,较好地实现了冷却塔大缩尺比模型对表面绕流高雷诺数效应的模拟;采用热线风速仪对冷却塔尾流进行测试,验证了由冷却塔整体气动力时程频谱函数确定涡脱频率方法的合理性;分析了环向断面阻力系数沿塔高的分布规律,在考虑相关性的基础上建议了冷却塔环向外表面的风压极值分布拟合曲线。在内压测试中,比较多种填料层透风率对于内压影响的基础上,采用相关性分析方法确定了内压极值分布规律。

冷却塔群塔刚体测压试验研究

在考虑冷却塔群塔和周围复杂建筑物场地条件下,通过冷却塔表面刚体测压试验,研究了双曲线型圆截面冷却塔表面雷诺数效应模拟、冷却塔表面气动压力分布特征;基于等效阻力系数表达式,研究了几种典型多塔组合工程场地条件下,群塔相对于单塔的等效风荷载比例系数,并进一步分析了冷却塔在最不利吹风工况中,位移、主拉、压应力分布关系。

大跨度缆索承重桥并列索尾流激振研究

近距离并列索（并列吊索和并列斜拉索）在大跨度缆索承重桥中应用广泛,下游索常会发生尾流致涡激共振、尾流驰振和尾流颤振等尾流激振。以间距为4 D（D为圆柱直径）的串列和错列双圆柱的尾流致涡激共振和尾流驰振为研究对象,在风攻角为0°~20°的条件下,主要通过风洞试验研究了下游圆柱发生尾流激振的起振条件、振动幅度和运动轨迹,研究了提高结构阻尼比的减振效果,讨论了尾流驰振的雷诺数效应,结合静止双圆柱绕流场的大涡模拟结果对尾流干扰机理进行了探讨。研究表明：在某些风攻角下,下游圆柱的尾流致涡激共振振幅远大于单圆柱涡激共振振幅;在0°以外的其他风攻角下,下游圆柱均发生大幅尾流驰振,但小攻角（5°和10°）与大攻角（20°）下的尾流驰振现象有明显差别,很可能存在不同的流场激励机理;风攻角为15°时,下游圆柱的尾流驰振有明显的雷诺数效应,其动力响应特性与经典驰振不同,下游圆柱起振后的振幅和运动轨迹随雷诺数（风速）的增大呈现复杂的变化形态;提高结构阻尼比可有效抑制下游圆柱的尾流致涡激共振,但对尾流驰振的减振效果不佳。