大风区铁路沿线挡风墙积沙机理及优化措施的风洞实验研究

位于兰州至新疆的兰新二线是世界上首条穿越大风区的高速铁路,途径著名的烟墩风区、百里风区、三十里风区及达坂城风区,风区段铁路里程长达 462.4 km,占新疆段线路总长的 65.1${\%}$,大风对铁路的运营、养护和运输造成很大危害. 为了降低大风对通行列车的危害,兰新铁路沿线设置了大量挡风墙. 挡风墙发挥作用的同时,也带来了铁路沿线的积沙问题. 为了解决这一工程实践的现实问题,本文提出了在现有挡风墙背风侧的不同位置处,设立第二道挡墙以减弱铁路积沙的治理思路,并开展了对应条件下对现有单道挡风墙、以及在现有单道挡风墙背风侧坡顶处和坡脚处设置第二道挡墙,共计3种情景的风洞模拟实验,发现设置第二道挡墙后距轨道线路高0.1 m处的沙粒水平速度、数密度、输沙通量及沉积率较无第二道挡墙时明显减少,介于8%$\sim$12${\%}$,51%$\sim$69${\%}$,20%$\sim$73${\%}$以及26%$\sim $38${\%}$,而且在现有单道挡风墙背风侧坡顶部增设第二道挡风墙的效果更好. 因此,本文的研究成果有助于优化大风区已有铁路沿线、城镇等防沙治沙工程措施.      

内埋武器高速风洞弹射投放模型试验关键技术研究

针对新一代战斗机超声速内埋武器弹射投放分离安全性问题,采用高速风洞投放实验技术研究内埋武器从开式武器舱弹射投放分离动态运动过程,风洞投放模型试验过程中采用除垂直加速度不足外,其余全部运动严格相似的轻模型相似设计方法,并针对轻模型法垂直加速度不足所导致的投放垂直位移偏离实物位移问题,采用一种简单易行的公式修正法进行补偿,试验给出了不同初始弹射投放分离条件下,内埋武器从载机投放分离后运动轨迹与姿态角随分离时间的变化规律,试验马赫数$Ma = 1.5$.研究结果表明:初始投放分离角速度对内埋武器投放分离后的运动轨迹及姿态角有较大的影响,当初始投放分离角速度$\omega _{z0}^s = 0^\circ/{\rm s}$时,内埋导弹出舱后先向下运动远离载机的流场干扰区,之后逐渐向载机方向抬升靠近并最终碰撞载机,高速风洞投放试验结果是不安全的,但经过公式修正后投放试验结果比较乐观,垂直方向运动仍然一直下降远离载机,这说明采用高速风洞投放试验得出的导弹不安全投放分离对真实载机来说不一定会出现,高速风洞投放试验结果比较保守. 当初始投放分离角速度$\omega _{z0}^s= 15^\circ/{\rm s}$和$\omega _{z0}^s = 30^\circ/{\rm s}$时,内埋导弹投放分离后运动趋势几乎一致, 均没出现向载机靠近的现象,内埋导弹具有一定的初始投放分离角速度有利于内埋武器的安全分离.      

非定常阵风场对沙粒跃移运动的影响浅析

野外阵风具有大尺度结构的非定常特征和小尺度结构的高频脉动特性,是造成风沙流输沙量波动和沙粒间歇性跃移的主要原因. 阵风的非定常性和脉动越显著,采用平均风速及沙粒粒径均一化分析风沙问题的误差越大,是野外观测、风洞实验及数值模拟的结果彼此偏差极大的主要因素. 野外阵风条件下的风沙跃移研究目前仍缺乏能够用于规范数学模型的有关阵风场和输沙率特征的可靠实时测量,有赖于风沙流整场高频测量技术和风洞模拟技术的发展.     

Study on Oxidation Mechanism of Nitrogen Monoxide in Indoor Environment

ＩｎｔｒｏｄｕｃｔｉｏｎＩｎｒｅｃｅｎｔｙｅａｒｓ ,ｔｈｅｓｔｕｄｙｏｎｔｈｅｅｆｆｅｃｔｏｆｉｎｄｏｏｒｌｉｇｈｔ ｃｏｎｃｅｎｔｒａｔｉｏｎｇａｓｅｏｕｓｐｏｌｌｕｔｉｏｎｔｏｈｕｍａｎｈｅａｌｔｈｉｓｄｅｅｐｌｙｃｏｎｃｅｒｎｅｄ .Ｔｈｅｍａｉｎｒｅａｓｏｎｉｓｔｈａｔ,ｗｉｔｈｔｈｅｐｅｒ ｆｅｃｔｉｎｇｏｆｔｈｅｉｎｄｏｏｒｇａｓｔｉｇｈｔｎｅｓｓａｎｄｈｅａｔ ｓｈｉｅｌｄｉｎｇｐｅｒ ｆｏｒｍａｎｃｅ ,ｔｈｅａｐｐｅａｒａｎｃｅｏｆｎｅｗａｒｃｈｉｔｅｃｔｕｒａｌａｎｄｄｅｃｏ ｒａｔｉ…     

双曲面屋盖的平均风压特点

通过风洞模拟实验对双曲面形屋盖的平均风荷载特点进行了研究.文中给出了屋盖的平均风荷载随风向角改变的变化特点和规律,特别讨论产生这些特点的原因及其流动机理.结果表明,在所有风向角下,双曲面屋盖除了在位于下游的边缘的挑檐位置外,都是负压分布.局部负压最大值主要出现在迎风挑檐的边缘部分.虽然屋盖的局部负压峰值随风向角改变,位置和数值变化都很大,然而,作为屋盖整体,平均风压平均值随风向角的变化很小.有关结果为类似建筑项目的风荷载设计和相应规范的制定和修改提供了有用的信息和材料.     

Design and veri?cation of airfoil families for large-size wind turbine blades?

For the design of wind turbine blades, the use of a family of specially tailored airfoils is particularly important. The dedicated airfoils can dramatically improve the capability of capturing wind power, reduce the structural weight to save the cost of manufacturing and transportation, and lower the inertial loads as well as the loads due to gust. An overview of the world-wide wind turbine airfoil families developed since 1990’s is presented, such as the S series, the DU series, the Ris? series, and the FFA series. The design and wind-tunnel tests of the Northwestern Polytechnical University (NPU) airfoil family for megawatt-size wind turbines, called the NPU-WA series, are summarized. All tests for the NPU-WA series are carried out in the NF-3 low-speed wind-tunnel with a two-dimensional (2D) test section of 1.6 m?0.8 m and at the Reynolds number ranging from 1.6?106 to 5?106 . The research activities for further improving the NPU-WA airfoils towards lower roughness sensitivity are also reviewed. The development of the new NPU-WA series dedicated for multi-megawatt wind turbines is discussed.     

细长锥边界层绊线转捩风洞自由飞试验

通过在半锥角θ_c=10°细长锥面上布置一定数量的人工绊线,促使细长锥表面边界层在相应轴向位置上发生层流向湍流转变的固定转捩,采用运动自由度不受约束的风洞自由飞试验技术研究边界层转捩对高超声速细长锥再入体无控自由飞行下的运动特性和气动特性影响规律,并与以往无人工绊线的细长锥风洞自由飞试验结果作对比.试验马赫数Ma=5.0,通过改变风洞前室总压P_0实现两个雷诺数的模拟,以模型长为特征尺寸自由流雷诺数分别为0.84×10~6和1.68×10~6.结果表明:当自由流雷诺数Re=0.84×10~6时,人工绊线尚不足以促使边界层发生转捩,有绊线的细长锥气动特性与无绊线基本一致,动稳定导数大于零;当自由流雷诺数Re=1.68×10~6时,人工绊线促使边界层发生固定转捩,细长锥的动稳定导数小于零,细长锥自由飞行动稳定.     

低湍流风洞

北京大学湍流研究室建成了一座精密的低湍流风洞,该风洞是一座能产生一股速度脉动和温度脉动都非常小的均匀气流的实验设备。技术关键是如何降低气流内的速度脉动值。由于风洞设计上采取了直流,闭口和吸入式的空气动力方案和其他正确技术措施,并精密加工,这样风洞就达到了气流均匀、平稳、湍流度低于0.08％的指标。风洞的实测值是0.05％左右。该风洞除可进行流动的稳定性,湍流发生的机理性基础实验外,还可进行一般的基础应用性实验,如减阻、风载、分离流动等实验研究。同时由于风洞很精密,也可以用作标定各类流速传感器的标准计量风洞。     

CFD analysis of the HyShot II scramjet combustor

The development of novel air-breathing engines such as supersonic combustion ramjets (scramjets) depends on the understanding of supersonic mixing, self-ignition and combustion. These aerothermochemical processes occur together in a scramjet engine and are notoriously difficult to understand. In the present study, we aim at analyzing the HyShot II scramjet combustor mounted in the High Enthalpy Shock Tunnel Göttingen (HEG) by using Reynolds Averaged Navier Stokes (RANS) and Large Eddy Simulation (LES) models with detailed and reduced chemistry. To account for the complicated flow in the HEG facility a zonal approach is adopted in which RANS is used to simulate the flow in the HEG nozzle and test-section, providing the necessary inflow boundary conditions for more detailed RANS and LES of the reacting flow in the HyShot combustor. Comparison of predicted wall pressures and heat fluxes with experimental data show good agreement, and in particular does the LES agree well with the experimental data. The LES results are used to elucidate the flow, mixing, self-ignition and subsequent combustion processes in the combustor. The combustor flow can be separated into the mixing zone, in which turbulent mixing from the jet-in-cross flow injectors dominates, the self-ignition zone, in which self-ignition rapidly takes place, and the turbulent combustion zone, located towards the end of the combustor, in which most of the heat release and volumetric expansion takes place. Self-ignition occurs at some distance downstream of the injectors, resulting in a distinct pressure rise further downstream due to the volumetric expansion as observed in the experiments. The jet penetration is about 30% of the combustor height and the combustion efficiency is found to be around 83%.