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.

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。

多参数变弯度翼型气动优化设计方法

为了获得机翼最优的气动外形,提出了一种多偏转参数与非均匀B样条结合的翼型前后缘连续偏转变形方法。以NACA3412翼型为研究实例,对翼型曲线进行参数化重构。以翼型前、后缘偏转位置和偏转角度为变化参数,模拟分析了不同变形状态对翼型气动特性的影响规律。以翼型升力系数和升阻比为优化目标,以前、后缘的偏转角度、偏转位置以及过渡段长度等六个偏转参数为设计变量,采用多目标遗传算法和ANSYS软件进行优化设计。结果表明,与基础翼型相比,优化后的变弯度翼型的升阻比提升约19.26%,升力提升约44.43%,明显改善了翼型的气动性能。

S型翼缝与尾缘襟翼联合控制风力机翼型气动性能的研究

降低叶片气动载荷对于延长风力机叶片寿命极为重要,尾缘襟翼是降低叶片气动载荷的一种有效手段,然而其在大攻角下对翼型的气动特性控制效果减弱。通过在50%叶片弦长处添加S型翼缝,采用数值模拟方法研究S型翼缝与尾缘襟翼联合调节风力机叶片气动特性的作用。利用剪切应力输运(shear stress transport,SST)湍流模型,计算模拟了S809翼型在雷诺数106下,S型翼缝与尾缘襟翼联合控制对翼型气动特性的影响,并分析了S型翼缝与尾缘襟翼的协同控制机理。结果表明,尾缘襟翼的偏转可显著改变翼缝槽内的气体流量,并有效调节叶片中部的压差,这种联合控制策略可在大攻角下大幅改善翼型的失速现象,从而显著增强尾缘襟翼对升力系数的调控能力。

NACA0021和NACA4822翼型肋通道中环境空气流动传热特性的实验研究

针对超燃冲压发动机在更高Mach数飞行时,主动再生冷却技术面临换热能力不足的瓶颈问题,拟利用翼型肋加强再生冷却通道的传热性能.为了从原理上验证翼型肋通道的强化传热效果,搭建了环境空气在NACA0021对称翼型肋和NACA4822非对称翼型肋通道(横截面尺寸50 mm×50 mm)中的流动传热实验测试平台,基于稳态液晶技术得到受热表面的Nusselt数.通过实验研究发现:NACA0021对称翼型肋通道和NACA4822非对称翼型肋通道的传热强度分别被提升了0.17%~17.1%和18.4%~52.1%,50 m^(3)/h流量下的PEC(performance evaluation criteri-on)分别为1.04和1.24;大流量条件下,NACA4822非对称翼型肋通道可强化中间受热面的传热性能;翼型肋通道中的流动压降也会相应增大,其中NACA4822翼型肋通道中的压降最大,翼型肋的非对称性使得流动湍流强度不断积累造成下游压降存在明显升高.该研究将有助于进一步开展翼型肋通道内超临界流体的流动传热特性研究,拓宽超燃冲压发动机主动再生冷却技术的应用温区.

基于UNet的翼型可压缩流场机器学习推理方法

为进一步提升高雷诺数、大迎角(Angle of attack,AoA)和高马赫数下的翼型可压缩流场预测精度和效率,本文提出了一种基于坐标转换方法和UNet神经网络的机器学习推理方法。首先,提出了用于数据前处理的坐标转换方法,将计算流体力学中的物理量和网格信息转换成神经网络空间信息,使流场信息的分布更符合神经网络的输入要求。其次,建立了新型深度UNet神经网络,使模型学习到翼型流场精细复杂的局部流动特征。本文将两种方法结合,建立了翼型可压缩流场机器学习推理方法,得到快速高精度的推理模型。最后,对不同种类翼型的流场与气动力进行预测分析,并与传统机器学习方法预测的结果进行比较。结果表明,本文提出的机器学习推理方法能够较好地预测翼型的可压缩流场,并且能够更好地捕捉高雷诺数下的复杂流动行为以及预测大迎角、高马赫数条件下的流动分离和激波现象。

U形渠道机翼柱型量水槽水力性能分析

为了详细探究机翼柱型量水槽应用于U形渠道的量水性能,设置了4个不同的量水槽收缩比开展水力性能试验。通过对流量、收缩比和上游水位等数据进行分析,拟合出机翼柱型量水槽的流量公式。研究还对测流精度、上游佛汝德数、临界淹没度等参数进行了详细分析。试验结果表明,机翼柱型量水槽水位~流量相关性极高,相关系数R^(2)达0.998,利用试验数据拟合出的流量公式简单易用,平均流量误差约为2.47%,上游佛汝德数小于0.3,临界淹没度最高为0.887。与传统的U形渠道量水槽相比,机翼柱型量水槽的流动公式简单易用,U形渠道机翼柱型量水槽的结构为进一步研究提供了新的思路和参考。

翼型悬浮抛光液动压流场的数值模拟

分析了盘式翼型悬浮抛光(ASP)的液动压分布规律,推导了工件盘和抛光盘不同心角速度反向等速条件下的液动压数学模型。对盘式翼型悬浮抛光流场进行了数值模拟,揭示了抛光盘和工件盘的运动关系以及抛光盘不同翼型曲线和迎角对流体动压力的大小和均匀性的影响规律。研究表明,当抛光盘和工件盘反向旋转时的流体动压力均匀性明显优于同向旋转,且当转速比为-1时流体动压力分布的数值模拟效果最佳;当选用NACA 16018翼型曲线、迎角为0°时,液动压带的面积数值效果最优。

翼型结构对印刷电路板换热器流动与换热特性影响

印刷电路板换热器(PCHE)作为超临界二氧化碳(S-CO_(2))布雷顿循环中的重要设备,其性能会影响系统的效率。为了提高翼型PCHE性能,探究翼型翅片结构对其流动与换热性能的影响。本工作针对S-CO_(2)布雷顿循环系统中的高温回热器,采用数值模拟的方法,选用S-CO_(2)为传热工质。通过对3种不同结构的NACA0020的翼型翅片通道的流动与换热性能进行比较,研究翼型翅片最大厚度在弦长上的位置参数对换热器的性能影响,并从热工水力性能、综合性指标、整体流动性、局部性能等方面分析了变化规律。结果表明,在翼型翅片结构中保持相对厚度不变的情况下,随着翼型翅片最大厚度在弦长上越接近翼型前缘的位置,其换热性能也会随之提高。其中NACA0020-20的翼型翅片通道在选定的工况条件下,j因子和Nu比其他两种翼型翅片通道大2.7%~8.8%和2.7%~8%,并且该翼型翅片结构可以有效地减小边界层所带来的影响,提高了其PCHE的换热性能,其综合性能更是优于其他两种翼型翅片。研究结果对于翼型PCHE的结构设计和性能优化提供了一定的依据。

混合相结冰条件下多段翼的撞击黏附与积冰的数值模拟

随着飞机结冰问题研究的深入,混合相结冰问题已经成为研究热点。本文使用了阻力模型、黏附模型和结冰热力学模型来计算混合相结冰条件下的准三维多端翼的结冰情况。首先对多段翼进行了网格划分和空气流场计算。然后进行了数值模拟计算,分析了混合相结冰条件下冰晶的撞击、黏附和积冰特征。结果表明,在本研究的条件下,冰晶的黏附质量流量很高,会对飞行安全造成威胁,并且冰晶在溢流水区域也会发生黏附。此外,随着液态水含量(Liquid water content,LWC)与总水含量(Total water content,TWC)比值的升高,冰晶更容易黏附在表面并参与表面结冰。

翼形表面流动激励载荷特征试验研究

为了研究水下航行体翼形表面流动激励载荷特征,采用柔性基底微型传感器阵列,建立风洞中翼形结构表面流动激励载荷测试方法。分析了翼形表面层流、转捩、湍流发展过程中激励力试验特征,试验结果表明:翼形表面经过层流、转捩、湍流发展过程,随着来流速度的增大,翼形表面转捩区位置逐渐前移直至完全湍流。提出了转捩点预报修正方法,修正后预报值与试验值偏差在10%以内,为水下航行体翼形流动激励力相关研究提供试验基础。

基于深度学习的翼型参数化建模方法

为解决现有翼型几何参数化描述方法优化设计效率低、计算工作量大的问题,提出了一种基于深度学习的翼型参数化建模方法。该方法以伊利诺伊大学厄巴纳-香槟分校(University of Illinois at Urbana-Champaign,UIUC)翼型数据库中翼型上下表面坐标点转化的翼型二维图像作为输入,首先使用卷积运算提取大量翼型图像的几何特征,然后通过多层感知机对提取的几何特征进行分类和压缩,将翼型形状压缩成若干个简化的拟合参数,最后通过解码器恢复翼型图像并输出翼型上下表面的点坐标。在此基础上,探讨了拟合参数数量对翼型几何精度的影响,确定了含6个拟合参数的卷积神经网络(convolutional neural network,CNN)结构,并基于计算流体力学数值仿真验证了所提出方法的拟合精度。最后,开发了可视化翼型几何设计软件,实现了拟合参数的调整与修正,并分析了各拟合参数对翼型形状的影响规律。结果表明,6个拟合参数均会对翼型形状产生全局影响,单独或联合调整6个拟合参数可获得新的翼型设计空间。研究结果可为翼型的优化设计提供技术支持与理论参考。