SURFACE OIL FLOW TECHNIQUE AND LIQUID CRYSTAL THERMOGRAPHY FOR FLOW VISUALIZATION IN IMPULSE WIND TUNNELS

This paper describes flow visualization techniques employing surface oil flow and liquid crystal thermography suitable for use in impulse wind tunnels.High spatial resolution photographs of oil flow patterns and liquid crystal thermograms have been obtained within test times ranging from 7 to 500 ms and have been shown to be very useful for revealing the detailed features of 3-D separated flow.The results from oil flow patterns,liquid crystal thermograms,schlieren photographs and heat flux measurements are shown to be in good agreement.

Analysis and Calibration of Internal Flow Force of EjectorPowered Engine Simulator System in Wind Tunnels

The ejector-powered engine simulator(EPES)system is an important piece of equipment in conducting an influence test of the intake and jet flow in low-speed wind tunnels.In this work,through the analysis of the structure and principle of EPES,three parts of the internal flow force were obtained,namely,the additional resistance before the inlet,the internal flow force in the inlet and the thrust produced by the ejector.On the assumption of one-dimensional isentropic adiabatic flow,the theoretical formulae for calculating the forces were derived according to the measured total pressure,static pressure and total temperature of the internal flow section.Subsequently,a calibration tank was used to calibrate the EPES system.On the basis of the characteristics of the EPES system,the process and method of its calibration were designed in detail,and the model installation interface of the calibration tank was reformed.By applying this method,the repeatability accuracy of the inlet flow rate calibration coefficient was less than0.05%,whereas that of the exhaust flow rate and velocity was less than 0.1%.Upon the application of the calibration coefficients to the correction of the wind tunnel experiment data,the results showed good agreement with the numerical simulation results in terms of regularity and magnitude before stall,which validates the reasonableness and feasibility of the calibration method.Analysis of the calibration data also demonstrated the consistency in the variation law and trend between the theoretical calculation and actual measurement of internal flow force,further reflecting the rationality and feasibility of the theoretical calculation.Nevertheless,the numerical difference was large and further widened with a higher ejection flow rate mainly because of the accuracy of flow measurement and the inhomogeneity of internal flow.The thrust deflection angle of EPES is an important factor in correcting this issue.In particular,the thrust deflection angle becomes larger with small ejection flow and becomes smaller with an increase in flow rate,essentially exhibiting a general change of less than 10°.

Numerical study on surrounding rock mass temperature field of Kangding tunnel no.2 considering wind flow

Based on the Kangding Tunnel No.2 project,this study analyzes the heat exchange between air and the rock mass surrounding the tunnel under wind flow by the finite difference method.The influence of factors on the temperature field of a tunnel in cold regions,including ventilation and initial conditions,is investigated.The results show that:1)The lower the air temperature,the greater the wind speed,the larger the rock mass temperature influence circle and the greater the frozen depth;2)When the wind speed is less than 3 m/s,its change has an obvious impact on the rock mass temperature;3)For every drop of 5C in air temperature,the frozen depth increases by about 5 m,indicating that the air temperature is an essential factor affecting the rock mass temperature regime;4)The higher the initial rock mass temperature is,the smaller the influence circle on the rock mass is.And to a certain extent,it determines the temperature distribution in the rock mass within a specific range from the wall surface.

A wind tunnel experiment of self-starting capability for straight-bladed vertical axis wind turbine

In this study,wind tunnel experiment was carried out to investigate the self-staring capability for straight-bladed vertical axis wind turbine.The flow visualization also was been performed at the rest of the rotor.The effect of the azimuthal angle of blade position relative to wind direction on the self-starting capability was discussed based on the results of flow visualization.The torque and centripetal force of the rotor when the self-starting behavior starts were roughly calculated with the flow visualization results of the rotor.It is suggested that there exists the condition of wind speed and configuration of the blade position of the rotor at the rest of rotor to the reach to situational rotation number.

一种基于直流式风洞的火星尘暴模拟装置

为了研究火星表面尘暴环境对探测器及人类活动的影响,研制了一种基于低密度直流式风洞的火星尘暴环境模拟装置:采用超声速引射器作为风洞动力源,结合具备多工况动态调节能力的大抽气量真空系统,实现了引射气量精准调控,可模拟100~1500 Pa低气压下的5~100 m/s大跨度风速;针对低气压下沙尘浓度难以精确控制的问题,采用振动式喂料、逆向螺旋式喷嘴设计以及大周期滞后串级调节方式,实现了0.1~1 g/m^(3)的沙尘浓度精确控制。该装置可用于研究火星尘暴环境对材料和机构的影响,同时还可用于火星气动力研究。

高速列车周围风雪运动特性及转向架区域积雪成因分析

采用基于Realizable k-ε模型的非定常雷诺时均方法(URANS)和离散相模型(DPM)研究高速列车底部转向架及其腔体区域的严重积雪问题。基于高速列车底部风雪两相流时空运动演化特性进行深入分析,并对转向架区域积雪成因进行归纳总结。研究结果表明:大量雪粒跟随转向架区域剪切层下方的高速气流流出转向架区域,部分雪粒在转向架中间区域和后端板附近跟随上扬气流向上扬起并撞击黏附在转向架和后端板迎风面,并在转向架底面形成大量积雪;仅有少量雪粒在后侧电机和后端板附近向上爬升至转向架上方,在后端板顶部相遇汇聚后在低速气流驱动下游离折返至前端板附近并重新汇入车底流场,悬浮雪粒在重力作用下沉积在转向架顶面,并在转向架上表面形成少量积雪。

大口径异型方管风量测量数值仿真分析及试验验证

针对1 m以上大口径异型方管转弯部分长度较短、前后段没有较长的直管,管道内部流场复杂、需准确测量管道流量的问题,进行了数值模拟分析。提出了一种基于变差系数的平均速度评价方法,选出多点最接近管道平均流速的位置,明确传感器插入深度和多个测量点的权重系数,拟合出1个以截面平均速度为函数,流场中多点的流速值为自变量的计算公式。在风洞实验台进行流量测量试验,并与数值分析拟合的公式计算值进行比较,满量程相对误差小于0.54%。

集装箱船上层建筑气动干扰特性与风阻优化

为优化具有多个尺寸巨大的上层建筑物集装箱船的风阻,本文以某20000TEU超大型集装箱船上层建筑为研究对象,开展风载荷和PIV流场测量风洞模型试验。根据得到的风阻与流场干扰特性,采用数值模拟对主体建筑纵向间距和局部构型进行优化布置,并通过风洞试验对优化结果进行验证。研究结果表明:主体建筑纵向间距是影响集装箱船风阻和甲板上方绕流场气动干扰的主要因素,合理调整上层建筑物纵向间距同时对建筑物棱角边缘倒圆角处理可以得到风阻性能更优的布置方案,经风洞试验验证,优化方案较初始方案风阻降低47.19%,具有较大优化空间,可为超大型集装箱船总布置设计提供参考。

仿生鲨鱼皮复合微纳减风阻结构的仿真与制备

仿生学与减阻技术的结合,为减阻开辟了重要的研究方向,在航空航天领域有着潜在的发展与应用前景。为提高降低风阻效果,本文对复合微纳减风阻结构进行了研究,基于仿生学原理,采用CFD仿真及激光微纳制造技术,建立了减阻结构组合模型,并在飞行器的大气传感器半球头体模型表面制造仿生鲨鱼皮复合微纳结构,即在仿生鲨鱼皮鳞片结构的基础上,通过激光干涉扫描二级微沟槽,以进一步提升减阻效果。采用CFD仿真与风洞实验相结合的方式,对减阻机理进行理论分析,完成了复合结构的微纳制造,减阻率最高可达10.3%。

汽车在环境风洞内流场的数值模拟与实验研究

为研究汽车在环境风洞内的流场特性,建立了环境风洞和整车数值模型,考虑了风洞喷口和收缩段的阻塞效应、边界层抽吸以及实验设施等对汽车流场的干扰效应,对环境风洞内汽车前方、车身和车轮周围、冷却模块以及机舱内的流场进行了数值模拟。对车身表面的静压以及车身周围和车底部的风速等进行测试,通过数值模拟结果与实验结果的对比,表明数值风洞能准确预测汽车在环境风洞内的流场特性。研究结果显示:汽车前端气流的速度分布沿着气流方向发生显著变化,越接近前端冷却模块时风速的均匀性变得越差;汽车底部气流受地面、车底和轮胎旋转等的共同影响呈现规律性的变化,车底风速沿车身纵向先增大后减小。本方法对研究汽车在环境风洞内的热气动性能以及开发数值风洞提供了新的思路和参考。

猫头刺盾状移动式固沙障防沙效应风洞模拟试验研究

[目的]猫头刺盾状移动式固沙障是运用仿生学原理,由盾状铁网筛与上方扎制固沙灌木猫头刺(Oxytropis aciphylla)茎叶构成的一种新型固沙障。对猫头刺盾状移动式固沙障的防风固沙效应进行试验,以确定最佳固沙障类型,并揭示其防风固沙机理,为野外工程防沙措施的选择和制定提供理论依据。[方法]通过风洞模拟试验,在6,10,14,18 m/s 4个风速条件下测量了猫头刺盾状移动式固沙障的风速流场,并在10,14,18 m/s 3个风速条件下对该固沙障进行了携沙风吹蚀试验。对照分析了原位自然型与不同类型,不同大小仿生猫头刺盾状移动式固沙障的防风沙效应。[结果](1)气流在经过猫头刺盾状移动式固沙障时速度均会减弱,形成明显的减速区。在6 m/s时,减速沉降区均达到了20 H(H为沙障高度,H=11 cm);随着风速增加,减速沉降区缩小。风速10与14 m/s时,减速沉降区为15 H;且在风速18 m/s时,也能维持15 H的减速沉降区。(2)3种风速梯度下,猫头刺盾状移动式固沙障的平均输沙量是无沙障的13.8%(10 m/s风速),21.1%(14 m/s风速),23.4%(18 m/s风速)。[结论]结构完整,直径更大的猫头刺盾状移动式固沙障具有最好的防风沙效果。该移动式仿生固沙障防风沙效果好,可移动,可组合并可机械化编制,在防治荒漠化、防风固沙领域有广阔的应用前景。

单线特长高铁隧道斜井长距离多工作面通风方案优选研究

秦岭马白山隧道属于特长双洞单线高铁隧道,其2号斜井工区共下辖斜井及正洞左右线大小里程5个工作面。针对工期紧、多工作面施工、洞内环境复杂的情况,隧道通风方式选择及通风效果关系到隧道施工进度、施工人员身体健康、工程造价等方面,因此选取合理的通风方式尤为重要。采用理论分析和数值模拟相结合的方法,建立三维数值模型,对施工通风的相关参数和隧道多工作面施工通风方案进行选型研究。通过理论计算,分析不同方案下风速和气体运移扩散规律,选配满足要求的通风机型及配置台数,解决了多工作面施工过程中风筒的布置问题。

真空吸入式风洞三维非定常流场时空特性

为了给真空吸入式风洞的气动优化设计提供参考,应用空气动力学知识和风洞理论,基于Fluent仿真平台,采用计算流体力学(CFD)有限元体积法求解雷诺时均方程(RANS),研究三维非定常流场的时空特性及其演化规律。通过建立收缩段和真空罐的数学模型,确定其特征参数;应用空气动力学知识,抽象流体的边界条件,构建全尺寸三维流体计算域;采用流体力学数值模拟方法,利用试验验证算法的置信度,并进行数值模拟。结果表明,当真空罐容积为2000 m^(3),真空度为3 kPa时可以较好地模拟悬挂发射装置在空中挂飞和投放瞬间的气动载荷。在试验段流场的核心区,其流场品质较好,可以提供0.80 Ma且至少1 s的稳定流场,满足0.40~0.80 Ma且维持至少500 ms稳定流场的设计要求。该研究结论可以为真空吸入式风洞的设计提供理论基础。

电弧风洞高焓流动模拟及壁面催化效应研究

对电弧风洞高焓流动进行模拟时,基于其高温复杂流场特性,对比不同热化学模型、壁面催化条件、流场一体化及分体计算等多种数值计算条件下,电弧风洞内部、出口流场特性及典型模型壁面热流分布。结果表明,模型距离喷管出口较近时,流场分体计算可以提高计算效率,但是模型距离喷管出口较远时,则必须采用一体化计算保证计算精度,数值模拟单温度热平衡模型计算得到的等热流模型表面热流高出双温度热非平衡模型6.99%。同时对电弧风洞高焓流动壁面催化效应开展研究,通过X射线扫描电镜对3组类型热流传感器表面元素成分进行分析,研究热流传感器表面催化属性对气动热测量的影响。结果表明,壁面催化效应会显著增加试验模型表面气动热环境,采用无氧铜基体的塞式量热计进行电弧风洞热流测量时,其表面会被氧化成CuO,数值模拟壁面采用有限催化条件γ=0.022时计算结果与试验结果更接近,也与文献中CuO的催化复合系数匹配。

搭载给水管的宽幅流线型钢箱梁涡振性能及抑振措施研究

为研究给水管不同设置位置对宽幅流线型钢箱梁的涡振性能影响及涡振抑制措施,以某大跨度扁平钢箱梁斜拉桥为研究对象,制作缩尺比为1:50的钢箱梁刚性节段模型进行风洞试验和数值模拟计算。首先对比分析了风攻角为0°、±3°时,给水管设置在主梁风嘴内(Ⅰ型)和设置在桥面上(Ⅱ型)两种不同断面形式的主梁涡振特性;并采用数值模拟探究了给水管对主梁涡振性能影响的作用机理。其次,研究了结构阻尼比对Ⅰ型断面主梁涡振性能的影响;最后,通过试验测试了栏杆透风率、栏杆抑流板等气动措施对Ⅰ型断面主梁涡振性能的影响。试验结果表明:给水管是涡振敏感构件,对于Ⅰ型断面,风攻角为-3°时,主梁未出现涡振现象;风攻角为0°时,有小幅涡振响应;风攻角为+3°时,出现明显的涡振现象;Ⅱ型断面主梁无涡振现象发生。数值模拟结果显示,给水管放置在主梁外部可以有效降低上表面旋涡的尺寸,从而抑制涡振的产生。增大结构阻尼比可以有效抑制主梁的涡振;改变栏杆透风率抑振效果不明显;设置抑流板对抑振效果明显。

风洞试验流场特性的模拟及分析

建筑围护结构相对于主体结构在风荷载作用下更易发生破坏,因此研究建筑周围流场对于结构抗风至关重要。通过组合不同形状、尺寸的流场试验装置研究流场分布特性,根据不同工况组合模拟出相同地貌下不同湍流度分布可控的流场,以及同一地貌下3种不同缩尺比在参考高度处流场分布特性一致的流场,为开展建筑围护结构表面风压分布特征及抗风措施研究奠定了可靠的基础。

Study on the characteristics of interaction flowfields induced by supersonic jet on a revolution body

The paper focuses on the triple jets interaction with a hypersonic external flow on a revolution body. The experimental model is a ogive-cylinder body with three supersonic nozzles, which are aligned along the flow direction. The freestream Mach numbers are 5 and 6. The spatial and surface flow characteristics are illustrated by the schlieren photographs and the typical pressure distribution. The results show that there are multi-wave system, separation, reattachment, multi-peak pressure, high-pressure and low-pressure zone boundaries obvious distinction in tri-jets interference flowfield. The present paper also analyzes how do the pressure ratio, the angle of attack, and Mach number effect on tri-jets interaction characteristics.

Aerodynamic Characteristics of Isolated Loaded Tires with Different Tread Patterns: Experiment and Simulation

The current research of tire aerodynamics mainly focus on the isolated and simplified tread tire.Compared with the real complex pattern tire,the tread pattern structure and deformed profile of a loaded tire has a greatly influence on tire aerodynamic drag.However,the mechanisms of the isolated loaded tires with different tread patterns effects on the aerodynamic drag are subjects worthy of discussion.The purpose of this study is to experimentally and compu-tationally investigate the aerodynamic characteristics of three tires 185/65 R14 with different patterns under loaded.A wind tunnel test model was first established using three-dimensional(3D)printing with a ratio of 1:1,and the pres-sure coefficients C_(p) of the three tires with different patterns are measured.The paper then conducted computational fluid dynamics(CFD)simulations for analyzing the pressure and flow characteristics.The accuracy of CFD simulation is verified by comparing the simulation results with the test results of pressure coefficients C_(p),and they are of good consistency.While,the general analysis of pressure coefficients C_(p) results of the three tires indicates high-pressure area on the windward surface,and occurrence of low-pressure area on the leeward surface,the pressure coefficients C_(p) of all three tires decreased firstly and then increased along in the air flow direction.The authors finally analyzed the effect of tread patterns on the flow field around the tire and revealed the differences between flow characteristics and aerodynamic drag.The results show that,angle of tire lateral groove has great effect on the flow field characteristics such that;the more the angle of lateral groove agrees with the air flow direction,the less the flow separation and flow vortices,and a minimum observable aerodynamic drag.The research provides a guidance for the design of low aerodynamic drag tires,and helps to illustrate the impact of tire aerodynamics on the car body in the future.

高马赫数内埋武器舱被动流动控制措施

高马赫数(Ma>2)武器舱剪切层更强、更稳定,其噪声产生机制与通常的亚、跨、超声速武器舱流动不同,导致用来抑制空腔噪声的流动控制措施也不同。分别采用数值模拟和风洞试验2种手段,研究了圆柱形机身和马赫数对空腔流动特性的影响,以及前缘锯齿、前缘立柱、前缘横柱、前缘挡板等不同被动流动控制措施对高马赫数武器舱声压级特性的影响,为高马赫数武器舱的流动控制措施设计和研究提供参考。研究表明:圆柱形机身对空腔底部的压力分布会产生影响,压力分布的不均匀性增大,后壁附近的压力峰值增大;对通常的亚、跨、超声速武器舱流动较为有效的被动流动控制措施,对高马赫数空腔流动效果不明显,甚至会加大武器舱内的噪声等级,需要开展更为深入的研究,以设计更为有效的流动控制措施。

汽车外后视镜造型对气动和噪声影响的风洞实验研究

为降低由汽车后视镜带来的气动噪声,本文以一简化汽车外后视镜模型为基础模型,提出3个不同造型改进方案:A造型模型镜身倾斜15°;B造型模型镜身倾斜30°;C造型模型将原圆柱形底座改为椭柱形底座。对4款造型外后视镜模型进行风洞实验研究,分析流场、空气阻力和壁面脉动压力随造型改变的规律。气动特性(流场和阻力)采用粒子图像测速仪(PIV)和六分量动态天平测量,声学特性采用壁面麦克风对侧窗平板的湍流脉动进行测量。研究结果表明:3个造型改进方案均可在不同程度上改善外后视镜尾迹区域流场品质,有效降低空气阻力和气动噪声。其中B模型阻力系数较基础模型降低18.4%,壁面脉动压力总声压级在中低频段可降低4.6 dB;C模型可降低阻力系数7.5%,总声压级可降低4.3 dB。