Airfoil friction drag reduction based on grid-type and super-dense array plasma actuators

To improve the cruise flight performance of aircraft, two new configurations of plasma actuators(grid-type and super-dense array) were investigated to reduce the turbulent skin friction drag of a low-speed airfoil. The induced jet characteristics of the two actuators in quiescent air were diagnosed with high-speed particle image velocimetry(PIV), and their drag reduction efficiencies were examined under different operating conditions in a wind tunnel. The results showed that the grid-type plasma actuator was capable of producing a wall-normal jet array(peak magnitude: 1.07 m/s) similar to that generated in a micro-blowing technique, while the superdense array plasma actuator created a wavy wall-parallel jet(magnitude: 0.94 m/s) due to the discrete spanwise electrostatic forces. Under a comparable electrical power consumption level,the super-dense array plasma actuator array significantly outperformed the grid-type configuration,reducing the total airfoil friction drag by approximately 22% at a free-stream velocity of 20 m/s.The magnitude of drag reduction was proportional to the dimensionless jet velocity ratio(r), and a threshold r = 0.014 existed under which little impact on airfoil drag could be discerned.

Influence of Flap Parameters on the Aerodynamic Performance of a Wind-Turbine Airfoil

A numerical method has been used to analyze the flow field related to a NACA 0015 airfoil with and without a flap and assess the influence of the flap height and angle on the surface pressure coefficient,lift coefficient,and drag coefficient.The numerical results demonstrate that the flap can effectively improve the lift coefficient of the airfoil;however,at small attack angles,its influence is significantly reduced.When the angle of attack exceeds the critical stall angle and the flap height is 1.5%of the chord length,the influence of the flap becomes very evident.As the flap height increases,the starting point of the separation vortex gradually moves forward and generates a larger wake vortex.Optimal aerodynamic characteristics are obtained for 1.5%(of the chord length)flap height and a 45°flap angle;in this case,the separation vortex is effectively reduced.

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.

Fourier neural operator with boundary conditions for efficient prediction of steady airfoil flows

An efficient data-driven approach for predicting steady airfoil flows is proposed based on the Fourier neural operator(FNO),which is a new framework of neural networks.Theoretical reasons and experimental results are provided to support the necessity and effectiveness of the improvements made to the FNO,which involve using an additional branch neural operator to approximate the contribution of boundary conditions to steady solutions.The proposed approach runs several orders of magnitude faster than the traditional numerical methods.The predictions for flows around airfoils and ellipses demonstrate the superior accuracy and impressive speed of this novel approach.Furthermore,the property of zero-shot super-resolution enables the proposed approach to overcome the limitations of predicting airfoil flows with Cartesian grids,thereby improving the accuracy in the near-wall region.There is no doubt that the unprecedented speed and accuracy in forecasting steady airfoil flows have massive benefits for airfoil design and optimization.

Design and Structure Optimization of Plenum Chamber with Airfoil Baffle to Improve Its Outlet Velocity Uniformity in Heat Setting Machines

The plenum chamber of a heat setting machine is a key structure for distributing hot air to different air channels.Its outlet velocity uniformity directly determines the heating uniformity of textiles,significantly affecting the heat setting performance.In a traditional heat setting machine,the outlet airflow maldistribution of the plenum chamber still exists.In this study,a novel plenum chamber with an airfoil baffle was established to improve the uniformity of the velocity distribution at the outlet in a heat setting machine.The structural influence of the plenum chamber on the velocity distribution was investigated using a computational fluid dynamics program.It was found that a chamber with a smaller outlet partition thickness had a better outlet velocity uniformity.The structural optimization of the plenum chamber was conducted using the particle swarm optimization algorithm.The outlet partition thickness,the transverse distance and the longitudinal distance of the optimized plenum chamber were 20,686.2 and 274.6 mm,respectively.Experiments were carried out.The experimental and simulated results showed that the optimized plenum chamber with an airfoil baffle could improve the outlet velocity uniformity.The air outlet velocity uniformity index of the optimized plenum chamber with an airfoil baffle was 4.75%higher than that of the plenum chamber without an airfoil baffle and 5.98%higher than that of the conventional chamber with a square baffle in a commercial heat setting machine.

Optimized Design of H-Type Vertical Axis Wind Airfoil at Multiple Angles of Attack

Numerical simulations are conducted to improve the energy acquisition efficiency of H-type vertical axis wind turbines through the optimization of the related blade airfoil aerodynamic performance.The Bézier curve is initi-ally used tofit the curve profile of a NACA2412 airfoil,and the moving asymptote algorithm is then exploited to optimize the design of the considered H-type vertical-axis wind-turbine blade airfoil for a certain attack angle.The results show that the maximum lift coefficient of the optimized airfoil is 8.33%higher than that of the original airfoil.The maximum lift-to-drag ratio of the optimized airfoil exceeds the maximum lift-to-drag ratio of the ori-ginal airfoil by 11.22%.Moreover,the power coefficient is increased by 12.19%and the torque coefficient of the wind turbine is significantly improved.

改变导叶翼型对水泵水轮机“S”特性的影响

针对水泵水轮机“S”特性区域的不稳定性问题,提出使用改型活动导叶翼型进行性能提升.以某水泵水轮机模型为研究对象,采用SST k-ω湍流模型对水泵水轮机全流道进行三维数值计算,通过对活动导叶翼型的改型设计,得出流量-转速模拟曲线,分析水泵水轮机组“S”特性改善情况.将计算与试验结果进行对比,并对改型活动导叶翼型前后机组的无叶区进行压力脉动分析.结果表明:在保证整体效率依然保持在92%附近的前提下,新的活动导叶翼型对机组的“S”特性依旧具有改善效果;无叶区压力脉动主要是受到活动导叶叶栅区域的分流在此重新聚集影响,并且与转轮叶片的动静相互扰动引起的;改型后的活动导叶降低了无叶区的压力脉动幅值,提升了水泵水轮机运行中的并网稳定性.

复杂地形对风速廓线的影响

随着风电利用的发展,越来越多的风电场建立在复杂地形的山区,为了更好地进行风能评估和风电预报,就需要了解复杂地形对风速廓线的影响。本文基于薄翼理论和湍流边界层扰动的线性化理论,采用两层模型对坡度较小的山地在其二维横截面上的风廓线进行了预测,该模型能够较为准确地预报地形、压力、稳定度对风速增速的影响,但对于三维地形或其他因素产生的风速的复杂变化,需要进一步将其扩展至三维,并结合数值模拟进行研究。

3D打印导板技术联合多次去旋转治疗重度僵硬性脊柱侧凸

背景:近年来,随着3D打印技术的发展,使得外科手术走向个性化、精准化。3D打印导板技术可实现术前规划、术中导航,使得外科手术更加精准。临床中重度僵硬性脊柱侧弯矫形术中仍面临置钉准确性不高导致螺钉松动甚至引起神经并发症的问题,现有关于3D打印导板技术指导重度僵硬性脊柱侧弯术中置钉的研究不多。目的:评价3D打印导向模板技术联合后路多次去旋转治疗重度僵硬性脊柱侧凸的临床效果。方法:回顾性分析3D打印导向模板椎弓根螺钉置入后联合施行后路多次转棒去旋转技术治疗重度脊柱侧凸6例患者的临床资料,男3例,女3例,手术时年龄15-23岁,平均(18.17±3.49)岁。分析术后2周和术后18个月时脊柱侧弯相关参数的变化,进行统计学分析。结果与结论:(1)手术时间280-540 min,平均(340.83±102.20)min,术中出血量1000-4000 mL,平均(2000.00±1073.70)mL,固定节段9-14个椎体,平均(11.83±1.72)个椎体,矫形过程中未出现螺钉松动;(2)所有患者均获得随访,术后2周全脊柱正侧位片显示冠状位主弯的cobb角、冠状面C_(7)铅垂线和S1正中线的距离、矢状面C_(7)铅垂线和S1后缘的距离、顶椎偏移、胸椎后凸角、腰椎前凸角均获得明显矫正,主弯的cobb角平均矫正率62.22%,术后18个月随访各参数较术后2周无明显变化,矫形效果满意,无感染和内固定断裂;(3)围术期切口延迟愈合1例,经过换药处理瘢痕愈合,未出现神经并发症;(4)结果表明3D打印导向模板结合后路多次转棒去旋转技术治疗重度僵硬性脊柱侧凸畸形安全有效,矫形效果满意。

液相剥离法高效制备石墨烯的研究进展

石墨烯是一种具有优良物理化学性质的二维纳米材料,广泛应用于电池、催化、传感器、印刷、生物医药等领域。然而,石墨烯及其衍生产品的应用与发展面临着巨大挑战——低成本、高品质、规模化生产。本文综述了液相剥离法高效制备石墨烯的研究进展,重点探讨了电化学插层法、溶剂插层法、高温膨胀法和微波膨胀法等液相剥离的前处理方法原理以及对石墨烯剥离效果的影响;分析了水基溶剂、有机溶剂和混合溶剂等剥离溶剂的优缺点与选取原则;对比了超声、高剪切和微通道等过程强化设备的剥离原理和优缺点;简述了离心分离的后处理方法以及分离效果;最后对液相剥离法宏量制备石墨烯的发展趋势进行了展望:通过结合人工智能等方法进行多目标优化,开发无残留的功能化插层剂并匹配温和快速的膨胀方法,寻找低毒、低沸点、高分散的溶剂体系,精确调控液相剥离设备作用机理,设计连续化梯级离心设备,实现液相剥离制备石墨烯的连续化、规模化、低成本快速制备。

正畸过程中牙齿三维方向变化的模型测量方法研究进展

牙齿三维方向上移动效率的评价是评估正畸疗效的重要内容之一。随着科学技术的发展,矫治器及矫正技术不断进步,用于研究正畸矫治牙齿三维方向移动效率的方法和工具也在不断更新。本文以牙齿移动测量方式发展为主线,介绍了由手工石膏模型测量转向利用计算机软件对数字化模型的测量过程和依据,并对三维数字化模型数据获取方式、储存文件格式及可选择的分析处理软件进行了说明,以及回顾了前人对三维数字化模型进行三维重叠的部分研究,总结了目前对光学扫描及X线扫描得到的两种三维模型数据常用的配准方法和配准区域的选择。

4D-Flow MRI在肥厚型心肌病左室流出道血流评估中的价值探索

目的 探索四维血流(four-dimensional flow,4D-Flow)磁共振成像(magnetic resonance imaging,MRI)技术在左心室腔内应用的可行性。材料与方法 本研究为前瞻性、横断面研究,纳入2022年8月至2023年1月于我院接受心脏MRI检查的21例肥厚型心肌病患者,采用3.0 T MRI扫描仪进行二维血流(tow-dimensional flow,2D-Flow)及4D-Flow成像,收集患者一周内进行的超声心动图检查结果。采用组内相关系数(inter-class correlation coefficient,ICC)、变异系数(coefficients of variation,COV)及Bland-Altman分析比较2D-Flow、4D-Flow评估左室流出道峰值流速的可重复性及一致性,并通过Pearson相关性分析探究二者与超声心动图测量结果的关系。结果 2D-Flow和4D-Flow观察者内/观察者间的ICC分别为0.999/0.999和0.995/0.992,COV分别为0.5%/0.5%和2.4%/2.6%。4D-Flow与超声心动图的测量结果呈中度相关,相关系数r值为0.574(P=0.006),但一致性较差,ICC为0.375(P=0.013)。2D-Flow与4D-Flow和超声心动图间无显著的一致性及相关性。结论 4D-Flow技术能够可视化心腔内血流模式,对左室流出道峰值流速的测量具有高度可重复性,且与超声心动图的测量结果具有显著的一致性。

二维超声联合剪切波弹性成像在老年肌少症诊断及疗效预测中的临床价值

目的探讨二维超声联合剪切波弹性成像在老年肌少症诊断及疗效预测中的临床应用价值。方法选取我院收治的84例老年肌少症患者(观察组)和同期42例健康老年人(对照组),两组均行二维超声和剪切波弹性成像检查,比较两组肌肉厚度、羽状角、肌束长度及收缩状态下腓肠肌杨氏模量平均值(以下简称杨氏模量值)的差异。观察组患者行常规药物治疗和弹力带训练,记录其治疗后总有效率,比较入院时与干预1、3、6个月后握力、四肢骨骼肌指数(ASMI)、简易躯体能力测试表(SPPB)评分的差异。绘制受试者工作特征(ROC)曲线分析二维超声和剪切波弹性成像参数单独及联合应用对老年肌少症诊断和疗效预测的效能。结果观察组肌肉厚度、羽状角、肌束长度及杨氏模量值均低于对照组,差异均有统计学意义(均P<0.05)。观察组患者治疗后总有效率86.90%(73/84);干预1、3、6个月后握力、ASMI、SPPB评分均高于入院时,差异均有统计学意义(均P<0.001)。ROC曲线分析显示,肌肉厚度、羽状角、肌束长度、杨氏模量值诊断老年肌少症的曲线下面积(AUC)分别为0.775、0.716、0.621、0.749,各参数联合应用的AUC为0.911,高于其单独应用,差异均有统计学意义(均P<0.05);肌肉厚度、羽状角、肌束长度、杨氏模量值预测老年肌少症疗效的AUC分别为0.805、0.846、0.785、0.775,各参数联合应用的AUC为0.889,高于单独应用,差异均有统计学意义(均P<0.05)。结论二维超声联合剪切波弹性成像在老年肌少症诊断及疗效预测中均有较好的临床应用价值,可为临床评估提供参考。

基于三维空间面积划分的轨迹相似性度量算法

针对大部分轨迹相似性度量算法无法区分方向相反轨迹的问题,提出了一种基于三维空间面积划分的三维三角分割(3TD)算法。首先,按照3TD算法的时间转换规则将轨迹集的绝对时间序列转变为相对时间序列;然后,在由经度、纬度以及时间三要素构成的三维空间坐标系中,通过划分规则将轨迹间面积分割成若干互不重叠的三角形,累加三角形面积并计算轨迹相似度;最后,在从船舶自动识别系统(AIS)收集的随机采样轨迹数据集上,与最长公共子序列(LCSS)算法和三角分割(TD)算法等进行了对比实验。实验结果表明:3TD算法对实验数据集中异向轨迹识别精确度达到100%;同时该算法面对海量数据集以及轨迹点部分缺失的数据集时,也能维持准确的度量结果以及较高的运算效率,能更好地适应异向轨迹相似度量工作。

基于双分支并联的特征融合电能质量扰动分类方法

为了提高对电能质量扰动信号(power quality disturbance signal,PQDs)在受到噪声和异常数据干扰时的分类准确率,提出了一种双分支并联特征融合网络的PQDs分类方法。首先,采用一维残差神经网络和一维卷积神经网络两个分支进行特征提取。然后,通过特征融合模块将这些特征融合在一起。最终,通过分类模块对PQDs进行准确分类。相对于串联神经网络,所提方法融合特征向量,增强了特征的区分度,同时适用于并行计算,进一步提高了识别速度。仿真结果表明,所提方法在叠加信噪比为13 dB、15 dB和18 dB的PQDs分类任务中,识别率均超过95%,此外,该方法对异常数据的分类效果也具有一定的鲁棒性。

翼型叶片安装方式对粉煤灰气力输送的影响

针对当前螺旋流气力输送中有关叶片安装方式的研究,分析了典型NACA系列翼型截面叶片应用于起旋装置时的流场。通过对观测面轴向流速与切向流速的仿真,计算叶片不同安装方式与安装角度时螺旋流场的旋流强度,确定了前缘迎风的安装方式比尾缘迎风起旋效果更强;安装方式固定时,旋流强度随安装角度的增大而减小。

风电NACA63418翼型参数化建模及优化

风力发电机的风轮气动效率与优良翼型的气动性能密切相关。以风力机传统翼型为研究对象,结合翼型参数化建模及自适应遗传算法,寻优搜索得到高性能优化翼型。比较了CST法和改进的Hicks-Henne型函数法对于NACA63418传统翼型的拟合精度,进而选用Hicks-Henne型函数法对NACA63418翼型进行参数化建模。通过自适应遗传算法和XFOIL软件耦合实现翼型气动特性的自动计算,提高翼形的设计效率,为翼型的理论设计拓宽了思路。

前缘圆柱对风力机翼型气动性能及冲蚀磨损影响研究

为研究风沙环境下流动控制方式对于NACA 0012翼型气动性能和冲蚀磨损的影响,通过在风力机翼型前缘布置微小圆柱来控制气流流动,采用离散项模型和SST k-ω湍流模型对控制翼型进行数值计算。结果表明:攻角较小时,微小圆柱处于X=0.04、Y=-0.03位置时控制效果最佳,可抑制流动分离,相比原翼型升阻比提高149.72%;微小圆柱处于X=0.02、Y=-0.02位置时翼型冲蚀磨损的减小量最大,相比原翼型减小97.66%;微小圆柱处于最优区域时翼型升阻比提高的同时冲蚀磨损量也会减小。

面向土地立体化管理的二三维地籍数据联动技术研究

城市化进程的加快和人口的爆炸式增长,造成城市土地资源日趋紧缺,人地矛盾逐渐凸显,推动城市由外延式扩张向纵向立体化发展转变,逐渐显现土地立体化利用的形态。本文分析了从规划选址阶段、土地审批阶段、土地供应阶段、不动产登记阶段等建设工程全周期的土地立体化管理所面临的技术挑战,研究并分别提出对应升维的建设思路,满足三维确权的不动产登记要求,为二维平面向三维立体转变提供建设性参考,有效支撑土地立体化管理。

基于InSe/MoTe_(2)异质结构的超灵敏宽光谱光电探测器

基于光栅效应的二维材料垂直结构可实现高灵敏度和宽光谱光探测器。本文报告了一种基于硒化铟(InSe)/二碲化钼(MoTe_(2))垂直异质结构的高灵敏度光电探测器,该探测器在365~965 nm波长范围内具有出色的宽光谱探测能力。顶层的InSe用作调节沟道电流的光栅层,MoTe_(2)则用作传输层。通过结合两种材料的优势,该光电探测器的响应时间为21.6 ms,比探测率在365 nm光照下可以达到1.05×10^(13)Jones,在965 nm光照下也可达到109 Jones数量级。外量子效率可达1.03×10^(5)%,显示出强大的光电转换能力。