具有多孔介质覆面层的柱体绕流流场分析

建立多孔结构覆面柱体绕流模型, 采用含Darcy-Brinkman-Forchheimer作用力项的格子Boltzmann方程对覆盖多孔介质层的方柱绕流进行数值模拟, 研究多孔介质对钝体绕流流场特性的影响。结果表明: 相比于不可渗透壁的柱体, 引入合适参数的多孔介质覆面层后可以有效降低其升力脉动幅值, 但阻力有所增加。同时, 较高雷诺数下多孔方柱的数值模拟表明: 多孔介质壁面使得尾迹区域的剪切层相距更远, 降低了尾流处湍动能, 并将雷诺应力的峰值移动到尾迹区域, 抑制了方柱两侧的动量交换, 使动量交换的位置发生在尾迹区域, 继而使得尾迹的涡街更加规则化。     

大口径空间反射镜Cartwheel型柔性支撑设计

针对同轴三反式空间光学遥感器对大口径主反射镜组件的高刚度、高强度、高热稳定性等特殊要求,提出一种基于Cartwheel型双轴柔铰的三点柔性支撑结构。首先利用无量纲方法研究了单个柔性支撑的柔度特性,然后利用有限元方法对反射镜组件的静力学、动力学与热特性进行灵敏度分析,确定了支撑结构中柔性环节的几何尺寸参数,并进行了有限元数值仿真。最后,利用面形值为λ/40均方根(RMS)的非球面镜进行了反射镜组件面形检测实验并利用等效球面镜组件进行了动力学实验。仿真与实验结果表明:当柔性环节尺寸为:壁厚t=8mm,直梁高度h=4mm,直梁长度L=8mm时,在正交三向自重与15℃稳态温升作用下,反射镜面形精度RMS小于12nm;反射镜组件一阶固有频率实验值为296Hz,与仿真结果相差6%,能够满足使用要求。     

大展弦比气弹机翼柔性非线性变形的气动力效应分析与风洞试验

从飞行器刚弹耦合动力学模型出发，引入柔性机翼准定常假设，建立大柔性飞行器非线性静气动弹性气动力方程，利用非线性迭代求解思路模拟了柔性飞行器的静气动弹性响应行为，开展了大展弦比飞机静气动弹性风洞试验验证，采用气动力有限基本解与机翼的耦合计算，发现了大柔性飞机大变形状态下载荷及结构变形形式随风速的变化规律.传统基于小变形假设的线性分析方法和刚体分析由于无法考虑气动面随结构变形的曲面气动力因素和结构变形后的非线性刚度特性，均与风洞试验存在一定的误差.对于大展弦比柔性飞机的非线性静气动弹性分析十分必要.      

薄膜自激拍打射流的流动特性实验

在射流喷嘴出口处安装一端固定的柔性薄膜,在流速足够大时,射流和柔性膜相互诱导产生自激拍打作用,针对这一现象,提出了一种新型的自激拍打射流混合技术。在直径D=40 mm的渐缩喷嘴上固定长度L=(0.5~2)D和厚度δ=50 μm的氟化乙烯丙烯共聚物(fluorinated ethylene propylene,FEP)薄膜,使用压差计测量了光滑渐缩喷嘴以及薄膜拍打运动所引起的压力损失。通过激光片光源和高速相机进行薄膜运动状态的显示和拍打幅度的测定,探究了拍打幅度受薄膜长度和Re的影响及其变化规律,利用测得的拍打幅度(A)和频率(f)作为Strouhal数(St=fA/U_o,U_o是射流的出口速度)的特征尺寸进行研究。在Re=3×104的条件下,使用热线风速仪测量了在不同薄膜长度下拍打射流轴向速度沿中心线的分布,并对湍流度、概率密度函数等特征进行分析。此外,经过数字迭代滤波后获得射流沿中心线的积分尺度、Taylor尺度和Kolmogorov尺度等统计量。实验结果显示,拍打射流的湍流度高于自由射流,意味着前者对周围流体具有更强的大尺度卷吸能力;但对不同薄膜长度的拍打射流而言,其湍流特性存在差异;在实验所用的薄膜长度范围内,1.25D膜长时射流混合效果最好。通过考察概率密度函数及其偏斜因子(Su)和平坦因子(Fu)发现,相较于自由射流,拍打射流速度更快地接近Gauss分布,这意味着拍打射流在增强大尺度卷吸的同时也促进了小尺度的掺混。      

脉动流方柱绕流特性研究

本文数值模拟雷诺数Re=100的条件下,脉动流振幅和频率分别为0.2≤A≤0.8和0≤f_P≤20 Hz时方柱绕流特性.通过数值计算得到方柱绕流的升、阻力系数,涡脱频率及尾涡特性,且稳定流下计算结果与文献结果一致。研究结果表明脉动流是一种有效的主动流动控制方法;在脉动流频率f_P为1.2~2.6自然涡脱频率f_(sn)时,旋涡脱落频率存在"锁定"现象;在锁定范围内,尾涡形成区域变短,时均阻力系数显著增大,且在脉动流频率等于两倍频率时,时均阻力系数达到峰值;随着振幅的增大,频率"锁定"范围增大。     

竖直圆管内超临界压力煤油传热特性实验研究

在压力2.5~4 MPa, 质量流量0.7~1.7 g/s, 热流密度0.06~1 MW/m2的实验条件下, 对煤油在内径1 mm, 长度300 mm竖直上升圆管内的流动与传热特性开展了实验研究, 并分析了传热系数随局部油温的变化及不同实验参数对传热的影响.结果表明, 超临界压力下煤油传热主要由自身物性和流动状态决定.超临界压力煤油传热过程大致可以分为3个区域:正常传热区传热强化区和传热恶化区.传热强化主要是湍流掺混增强和近壁面流体在拟临界温度附近物性剧烈变化的综合作用; 传热恶化则是因为壁温及近壁面流体温度远高于拟临界温度, 在近壁面发生了类似于亚临界状态下的“拟膜态沸腾”.      

超临界压力煤油传热不稳定实验研究

在压力2.5~4 MPa, 质量流量0.7~1.7g/s, 入口温度20~250 ℃的实验条件下, 对煤油在内径1 mm, 长度300 mm竖直上升圆管中的流动及传热不稳定现象进行了实验研究.结果表明, 当热流密度增大到一定程度后, 传热不稳定开始发生.不稳定发生的起始热流密度随压力和流量的增加而增大, 随入口油温的升高而减小, 且当入口油温升高到一定程度后无不稳定现象发生.不稳定发生的初始时刻, 出口油温迅速增加, 管道壁温明显下降, 传热系数增大; 实验段局部流速增大, 进而在管道内部形成压力脉动并产生声音.不稳定结束后, 出口油温几乎保持不变, 壁温会缓慢增加, 直至下一次不稳定发生.      

气液两相流中旋涡诱发方柱和正三角柱振动时的脉动升力研究

垂直上升矩形截面管内的气液两相流横向冲刷水平布置的柱体时,一定条件下会在柱体后部产生旋涡交替脱落现象,使柱体在与来流垂直的方向上受到脉动升力的作用。本文以截面分别是方形、正三角形的柱体为例,研究了这种带锐缘的柱体在气液两相流中受到的脉动升力,得出了涡街的Strouhal数和柱体的脉动升力系数C'L随Re数和来流含气率。的变化情况。实验结果表明：在本文的实验范围内,方形柱体和正三角柱体的Strouhal数不随Re数变化,而在一定的含气率范围内,随着含气率的增大而增大;C'L也不随Re数而变化,而随着来流含气率的增大相减小而后很快增大。     

栅中空化水翼的水动力特性

采用实验的方法研究了栅中水翼的空化水动力特性.实验在空化水洞中完成,采用高速摄像技术观测了不同空化阶段的空穴形态,并测量了栅中水翼所受的升阻力.结果表明:在空化没有发生时,栅中水翼所受升阻力随雷诺数的增加而增大;当空化产生时,不同的雷诺数下栅中水翼空化动力特性随a/2a的变化趋势一致;在相同的雷诺数下,当4>σ/2α>2.8时,栅中水翼升力系数变化的频率基本不随σ/2α改变,最大空穴长度小于水翼弦长,此时St=0.11;当σ/2α<2.8时,栅中水翼升力系数变化的频率增加,对应的St=0.28.     

光学炮塔气动载荷的非稳态特性

采用耦合J-B模型的IDDES模型与双时间步LU-SGS方法开展炮塔非稳态气动载荷的数值仿真研究。炮塔流动会发生分离,天顶位置的分离角大于90°;当流动绕过炮塔时,形成马蹄涡、脱落涡街等非稳态流场结构,导致气动载荷也具有非稳态特性;炮塔顶点的脉动静压功率谱在1.6~40.0 kHz进入各向同性均匀湍流的惯性子区,基本满足Kolmogrov的-5/3定律;气动力以阻力为主,横向力的脉动幅值大,气动力矩则以俯仰力矩为主,滚转力矩的脉动幅值大,偏航力矩可以忽略不计;气动力和力矩的功率谱主要集中在1 kHz以下,存在多个尖峰频率,主频约为230 Hz (斯特劳哈尔数为0.15)。在ATP系统设计之初,需要考虑光学炮塔所受气动载荷的非稳态特性,并规避尖峰频率尤其是主频的谐振破坏问题。     

Wind excited vibration of a square section cantilever beam in smooth flow

The self-excited oscillation of a flexible, square section, slender, cantilever beam in a uniform, smooth wind stream is examined experimentally and theoretically. The excitation was due to negative damping type aerodynamic forces and the amplitude was limited as forces became non-linear. Steady oscillations occurred only when a face was oriented less than 15 degrees to the free stream velocity. Theoretical solutions based on measured quasi-static air forces agreed qualitatively with the experimental results, but failed to predict some peculiar drop-off behavior observed in the experiment. Discrepancies were attributed to slight irregularities in the cross-section shape of the beam.     

Flow characteristics around a square cylinder with changing chamfer dimensions

Abstract  

It is known that for a square cylinder subjected to uniform flow, the drag force changes with the angle of attack. To clarify the flow characteristics around a square cylinder with corner cutoffs, we measured the drag coefficient and the Strouhal number for changing chamfer dimensions. We analyzed the flow around a square cylinder with corner cutoffs by applying the RNG k–ε turbulent model, and investigated the surface flow pattern using visualization by means of the oil film and mist flow method. From these results, we obtained the surface flow patterns by the oil film method and numerical analysis. The numerical results agreed well with the experimental values. The drag coefficient of the square cylinder with corner cutoffs decreased suddenly at an angle of attack of about α = 0°– 10° when compared with the drag coefficient for a square cylinder. The minimum value of the drag coefficient for the square cylinder with corner cutoffs decreased by about 30% compared with that for the square cylinder. The drag coefficient of the square cylinder with 10% corner cutoffs was found to be smallest, since the wake area of this square cylinder was smaller compared with that of the other square cylinder.     

Prediction of aerodynamic noise reduction by using open-cell metal foam

As the speed of high-speed train (HST) increases continuously, aerodynamic noise has become more remarkable compared with the wheel/rail noise, which affects the inhabited environment along the railway and the riding comfort. This paper preliminarily investigates the feasibility of using open-cell metal foam covering layer to reduce the low Mach number aerodynamic noise generated by the flow around a circular cylinder which is the typical section of pantographs. The aerodynamic noises radiated from the circular cylinder with and without metal foam are calculated. The hybrid method combining two-dimensional large eddy simulation (LES) with Ffowcs Williams–Hawkings (FW–H) equation is employed. The calculated Strouhal number, time-averaged drag coefficient, base pressure and overall sound pressure level agree well with some available experimental data. Then, the influences of metal foam porosity, pore density, thickness of covering layer and the speed of train on the aerodynamic noise and the aerodynamic forces are investigated, and some detailed comparisons of flow field are made. The numerical results indicate that as a passive scheme, the open-cell metal foam with high porosity can modify the flow, adjust the vortex shedding frequency and regularize the wake, leading to a significant reduction of aerodynamic noise. The results are expected to provide useful information for the control of aerodynamic noise using this new material.     

A fluid–structure interaction model of insect flight with flexible wings

We present a fluid–structure interactions (FSI) model of insect flapping flight with flexible wings. This FSI-based model is established by loosely coupling a finite element method (FEM)-based computational structural dynamic (CSD) model and a computational fluid dynamic (CFD)-based insect dynamic flight simulator. The CSD model is developed specifically for insect flapping flight, which is capable to model thin shell structures of insect flexible wings by taking into account the distribution and anisotropy in both wing morphology involving veins, membranes, fibers and density, and in wing material properties of Young’s modulus and Poisson’s ratios. The insect dynamic flight simulator that is based on a multi-block, overset grid, fortified Navier–Stokes solver is capable to integrate modeling of realistic wing-body morphology, realistic flapping-wing and body kinematics, and unsteady aerodynamics in flapping-wing flights. Validation of the FSI-based aerodynamics and structural dynamics in flexible wings is achieved through a set of benchmark tests and comparisons with measurements, which contain a heaving spanwise flexible wing, a heaving chordwise-flexible wing with a rigid teardrop element, and a realistic hawkmoth wing rotating in air. A FSI analysis of hawkmoth hovering with flapping flexible wings is then carried out and discussed with a specific focus on the in-flight deformation of the hawkmoth wings and hovering aerodynamic performances with the flexible and rigid wings. Our results demonstrate the feasibility of the present FSI model in accurately modeling and quantitatively evaluating flexible-wing aerodynamics of insect flapping flight in terms of the aerodynamic forces, the power consumption and the efficiency.     

蒸汽爆炸粗混合过程中的蒸发阻力模型

在蒸汽爆炸的粗混合过程中,由于液体的快速蒸发,高温金属液滴的周围会产生一层很薄的蒸汽膜,此时液滴周围的边界层流动与没有液体蒸发时有很大的不同,因此,常温情况下的小球在连续液体中运动时的通用阻力模型在这种情况下是不适用的．本文通过受力分析,考虑了高温小球受力的分布和表面蒸发对小球周围力的影响,从阻力的基本机理上分析了蒸发状态下小球的运动阻力,分别提出了高温颗粒穿过自由表面时与其在液体中运动时的蒸发阻力模型．分析表明,当小球温度高于2500 K,特别是在靠近自由表面的区域,由于小球表面液体蒸发而产生的蒸发阻力作用非常明显．分析指出,小球的入水初速、小球表面的液体蒸发速率以及汽膜厚度都是影响小球运动阻力大小的重要因素．     

Integrated modeling of insect flight: From morphology,kinematics to aerodynamics

An integrated and rigorous model for the simulation of insect flapping flight is addressed. The method is very versatile, easily integrating the modeling of realistic wing–body morphology, realistic flapping-wing and body kinematics, and unsteady aerodynamics in insect flight. A morphological model is built based on an effective differential geometric method for reconstructing geometry of and a specific grid generator for the wings and body; and a kinematic model is constructed capable to mimic the realistic wing–body kinematics of flapping flight. A fortified FVM-based NS solver for dynamically moving multi-blocked, overset-grid systems is developed and verified to be self-consistent by a variety of benchmark tests; and evaluation of flapping energetics is established on inertial and aerodynamic forces, torques and powers. Validation of this integrated insect dynamic flight simulator is achieved by comparisons of aerodynamic force-production with measurements in terms of the time-varying and mean lift and drag forces. Results for three typical insect hovering flights (hawkmoth, honeybee and fruitfly) over a wide rang of Reynolds numbers from O(10²) to O(10⁴) demonstrate its feasibility in accurately modeling and quantitatively evaluating the unsteady aerodynamic mechanisms in insect flapping flight.     

Investigation of a hybrid approach combining experimental tests and numerical simulations to study vortex-induced vibration in a circular cylinder

In this study, a hybrid approach based on computational fluid dynamics (CFD) was used to investigate the aerodynamic forces associated with vortex-induced vibration (VIV) in a circular cylinder. The circular cylinder and the flow field were considered as two substructures of a system. Circular cylinder motion was produced in a wind tunnel test of the VIV prior to the numerical simulation; this motion was used as a known cylinder boundary condition and applied to the flow field. The flow field with the known moving boundary condition was then numerically simulated by the ANSYS CFX code. The transient aerodynamic coefficients of the circular cylinder with predetermined motion were obtained from the numerical simulation. To verify the feasibility and accuracy of the proposed hybrid approach and to calculate cylinder vibrations, the transient aerodynamic coefficients were applied to a single degree of freedom (SDOF) model of the circular cylinder. The oscillation responses of the circular cylinder from the calculated (SDOF model) and experimental results were compared, and the results indicate that the hybrid approach accurately simulated the transient aerodynamic coefficients of the circular cylinder. For further comparison, a nonlinear aerodynamic coefficient model based on a nonlinear least square technique was applied to the SDOF model. The nonlinear aerodynamic model can predict well the amplitude and lock-in region of the VIV of the circular cylinder model.     

Use of the wake of a small cylinder to Control unsteady loads on a circular cylinder

Simultaneous measurements of lift and drag forces have been performed in order to study passive control of unsteady loads induced on a circular cylinder. For this purpose, an aerodynamic balance has been developed. The balance, developed for a cylinder of 25.4 mm in diameter, was designed to operate in the subcritical regime (Re=32000). This instrument is characterized by its sensitive element that forms a small central part of the cylinder. The static and dynamic calibrations of the balance show the appropriateness of the present design. Moreover, qualification experiments carried out with a single cylinder gave results (mean and rms values of the lift and drag coefficients) that are in good agreement with those found in the literature. The purpose of this paper is to present a passive control experiment performed by means of the wake of a smaller cylinder interacting with a larger one. Firstly, a parametric study was performed by varying the following: i) the diameterdS of the small cylinder for one large cylinder diameterd (7 values in the range 0.047≤d _S /d≤0.125); ii) the center-to-center spacingS/d (11 values in the range 1.375≤S/d≤2.5); and iii) the stagger anglea(0≤a≤90 with a fine angular stepDa fora≤15). A maximum mean drag reduction of about 48% is achieved. Ata=4 to 8, one can observe a peak of mean lift coefficient. Then unsteady fluid forces, vortex shedding frequency and flow pattern were systematically investigated for the small cylinder having a diameterdS=2.4 mm (0.094d). Reductions of 78% and 56% of the rms lift and drag fluctuations respectively were obtained with the small cylinder placed at a slight stagger angle in the range 6<a<9. This leads to an instantaneous force vector that exhibits more steadiness both in angle and amplitude. Moreover, at these stagger angles, the energy of the lift fluctuations at the shedding frequency is significantly reduced compared to the single cylinder case.     

Micro-force measurement of drag on a small flat plate in the presence of a corona discharge

The design of a micro-force sensor suitable for the measurement of corona drag and other low velocity drag studies in a small laboratory wind tunnel facility is described. Example drag data are given for dc corona discharge generated by sharp parallel electrodes mounted on a microscope glass slide with discharge parallel to the air flow. The arrangement simulates two-dimensional flow over a flat plate useful for theoretical analysis. Measurements of free stream wind velocities in the range 0–210 cm/s with attendant drag down to 10⁻⁷ N can be detected in this facility depending on the calibration. The force sensor utilizes two strain gages mounted on a 0.127 mm stainless steel “feeler gage” in a cantilever arrangement. A bridge circuit provides sensitivities in the range 40–250 N/mV using a gravitational calibration technique. Anomalous effects from suspension wires and the interaction of electrostatic forces with the surroundings are discussed.