基于iSIGHT平台的三维机翼气动优化设计

基于iSIGHT设计平台,结合CFD软件Fluent对三维机翼进行多目标优化设计,以提高其气动性能．设计过程中采用NCGA(neighborhood cultivation)——邻域培植遗传算法,NSGA-Ⅱ(non-dominated sorting)——非支配解排序遗传算法为优化算法,以N-S方程作为主控方程,对三维机翼优化．经过优化设计后结果表明,机翼的气动性能有了显著改善,该优化方法可推广用于多种翼型和机翼优化．     

等速上仰翼型流动结构的实验研究

本文用流动显示方法细致地观察了等速上仰翼型的非定常流动现象,通过多种布置产生氢气泡鉑丝的方法,清楚地显示出了等速上仰翼型的流动结构。研究了前缘涡、剪切涡和尾部流动结构随着时间的演变及它们之间的相互作用。还研究了转速对流动结构的影响:在不同的转速变化范围内,会出现不同的流动结构。并结合旋涡动力学理论,探讨了翼型上仰过程中高升力产生的原因和动态失速机理。     

关于绕任意机翼非定常流动的一种无条件稳定的欧拉方程解

本文给出了绕二维与三维刚性或弹性振动机翼非定常无粘流动的欧拉方程解。首先利用Ｊａｍｅｓｏｎ的有限体积方法建立了求解欧拉方程的Ｒｕｎｇｅ－Ｋｕｔｔａ方法。为了提高受Ｒｕｎｇｅ－Ｋｕｔｔａ法稳定性限制的时间步长，文中采用了变系数的残值光顺方法。该方法避免了常系数残值光顺引起局部流场损失较大的问题。同时可在保证原计算格式精度要求下，大幅度提高计算时间步长，从而提高了计算效率。文中以二维与三维矩形机翼为例，分别对其在跨音速流场中作则性或弹性振动的非定常气动力进行了计算，研究了不同振动频率对流动产生的影响。部分计算结果与相应实验结果进行了比较。结果证明本方法是可靠的，可以用于求解绕任意运动机翼非定常流动问题。     

三维振荡机翼含激波跨声速非定常绕流广义变分原理的普遍形式及其派生族

本文在文献[1,2]基础上,建立了作任意周期性振荡的三维机翼含激波非定常跨声速绕流的广义变分原理普遍形式及其派生族。为了便于数值处理及捕获未知间断面,文中运用变域变分工具将振荡的激波及自由尾涡面上的间断条件(包括Rankine-Hugoniot激波关系)以及几乎全部边界条件都转化成自然界面条件,并兼顾了翼面吸(喷)气的作用。本文为引进有限元法等变分解法提供一更普遍、完善的理论基础,并可再推广到三维机翼-机身组合体和三维旋转叶栅上去。     

随机环境中的分枝过程

本文综述性地介绍了随机环境中分枝过程的产生、发展、其主要结果以及研究动态．     

二维平板可压缩边界层的二次稳定性分析

本文在二维可压缩边界层中应用Ｆｌｏｑｕｅｔ分析,建立了控制次谐波稳定性的方程组,研究在二维可压缩边界层转捩过程中二维有限振幅的Ｔ＿Ｓ波对三维线性小扰动的作用,并计算了来流马赫数对次谐波的产生和发展情况的影响,从中可以看出二维和三维扰动波相互作用对二维可压缩流动边界层的发展过程所产生的影响     

风力机叶型增升及叶尖流动控制研究

研究了两种改善风力机叶型气动性能的流动控制技术,分别对风力机专用S809翼型和较大升阻比的FX 60-100翼型进行应用研究．首先,通过在叶型前缘加装流动偏转器,研究流动偏转器对叶型流动分离的控制效果．并采用多岛基因算法,对流动偏转器进行多参数优化．结果表明:流动偏转器可以有效控制叶型的失速特性,推迟失速攻角和增加升力;基因优化算法能更大地提升流动偏转器的控制效果．其次,基于对风力机叶尖旋涡和尾涡特征以及叶片表面压力分布的分析,在叶片尖部加装不同倾斜角的旋涡扩散器控制叶尖涡．结果表明:涡扩散器能够提高叶尖涡涡核的总压,削弱其旋涡强度,使风力机尾流旋涡耗散更快,从而可以减小噪声,提高叶片效率．     

湍流度对翼型绕流影响的数值模拟及与实验的对比

研究了NACA0012翼型在低Reynolds数不同湍流度下的空气动力学特性．既运用了有限谱法和QUICK格式相结合的数值计算方法,又通过实验手段,研究了湍流度对流场的影响,并得到了计算与实验相符的结果．计算结果说明了有限谱法的高精度及与其他格式结合后应用的灵活性．对翼型受力和流场的结果分析显示:低湍流度下无明显的失速特征,高湍流度下失速特征明显;湍流度还对边界层后的剪切层有很大影响,高湍流度的受力特征和流场结果与高Reynolds数下的情形相似．     

复合材料层合板低速冲击后压缩的损伤累积模型

为了分析复合材料层合板低速冲击后的压缩性能，首先用三维动态有限元素法对两种层合板进行了低速冲击损伤模拟计算，以此作为冲击后压缩(CAI)层合板的初始损伤，然后用三维静态有限元对含损伤的层合板进行压缩破坏模拟和剩余强度计算，从而实现了层合板从冲击损伤到压缩破坏损伤全过程的模拟．结果表明，损伤投影面积和CAI强度的计算值与试验结果有较好的一致性．     

基于外场实验的风力机叶片三维效应研究

针对一台33 kW水平轴风电机组开展了外场实验,得到其叶片7个断面翼型的压力分布曲线;基于求解时均N-S方程对风轮进行三维数值模拟,以及将叶片各断面作为二维翼型进行数值计算,分别得到各断面翼型的压力分布曲线及升阻力系数．通过将外场实验、三维和二维数值计算所得压力分布曲线及升阻力系数进行对比分析,研究了三维效应对风力机气动性能的影响．研究表明,从叶尖到叶根各断面翼型的压差先增大后逐渐减小,叶片表面压力分布曲线比较明显地反映了从叶尖到叶根流动分离的变化;叶片表面压力分布的三维数值计算结果较二维计算结果更加接近于外场实验值;风力机叶片表面的三维流动对叶片的气动性能影响较大,在叶尖和叶根部分尤为突出.     

An insight into the rotational stall delay

Blade element momentum (BEM) theory which is based on the two-dimensional (2D) aerodynamic properties of airfoil blade element is the most common computational engineering method for the prediction of loads and power curves of wind turbines. Although most BEM models yield acceptable results for high tip-speed ratios where the local angles of attack are small, no generally accepted model exists up to date that consistently predicts the loads and power in stall regime for stall-controlled turbines. Understanding of the stall delay phenomenon on wind turbines remains, to this day, incomplete. The lack of a conceptual model for the complex three-dimensional (3D) flow field on the rotor blade, where stall is begins, how it progresses and where stall is practically terminated, has hindered the finding of a unanimously accepted solution. The paper aims at giving a better understanding of the delayed stall events and a reasonably simple correction model that complements the 2D airfoil characteristics used to a BEM method. (© 2012 Wiley-VCH Verlag GmbH & Co. KGaA, Weinheim)     

Dynamic Stall Measurements

Forces acting statically on an airfoil in laminar flow are well known. Under turbulent conditions dynamic effects (like dynamic stall) take place. There are different theoretical models to describe dynamic stall, but very little experimental data. We present dynamic stall measurements using an FX 79-W-151A airfoil in a closed test section of a wind tunnel with laminar inflow. Dynamic stall was induced by pitching the foil sinusoidally. Lift forces were measured using the pressure distribution on the wind tunnel walls. (© 2009 Wiley-VCH Verlag GmbH & Co. KGaA, Weinheim)     

昆虫翼拍动中受载变形的粘弹性本构模型

昆虫翼拍动受载时发生被动变形，被看作为有助于改善飞行性能的机制之一。决定这种被动变形大小的一个关键因素是昆虫翼的材料本构关系，至今缺乏研究，基于蜻蜓翼（离体）的应力松弛实验和模型翼拍动时受载变形的有限元数值分析，揭示了粘弹性本构关系是昆虫翼材料性能的合理描述，并研究了粘弹性参数对被动变形的影响。     

Helicopter blade flapping with and without small angle assumption in the presence of dynamic stall

The flapping equation for a rotating rigid helicopter blade is typically derived by considering (1) small flap angle, (2) small induced angle of attack and (3) linear aerodynamics. However, the use of nonlinear aerodynamics such as dynamic stall can make the assumptions of small angles suspect as shown in this paper. A general equation describing helicopter blade flap dynamics for large flap angle and large induced inflow angle of attack is derived. A semi-empirical dynamic stall aerodynamics model (ONERA model) is used. Numerical simulations are performed by solving the nonlinear flapping ordinary differential equation for steady state conditions and the validity of the small angle approximations are examined. It is shown that the small flapping assumption, and to a lesser extent, the small induced angle of attack assumption, can lead to inaccurate predictions of the blade flap response in certain flight conditions for some rotors when nonlinear aerodynamics is considered.     

Numerical bifurcation analysis of static stall of airfoil and dynamic stall under unsteady perturbation

By the finite element method combined with Arbitrary-Lagrangian-Eulerian (ALE) frame and explicit Characteristic Based Split Scheme (CBS), the complex flows around stationary and sinusoidal pitching airfoil are studied numerically. In particular, the static and dynamic stalls are analyzed in detail, and the natures of the static stall of NACA0012 airfoil are given from viewpoint of bifurcations. Following the bifurcation in Map, the static stall is proved to be the result from saddle-node bifurcation which involves both the hysteresis and jumping phenomena, by introducing a Map and its Floquet multiplier, which is constructed in the numerical simulation of flow field and related to the lift of the airfoil. Further, because the saddle-node bifurcation is sensitive to imperfection or perturbation, the airfoil is then subjected to a perturbation which is a kind of sinusoidal pitching oscillation, and the flow structure and aerodynamic performance are studied numerically. The results show that the large-scale flow separation at the static stall on the airfoil surface can be removed or delayed feasibly, and the ensuing lift could be enhanced significantly and also the stalling incidence could be delayed effectively. As a conclusion, it can be drawn that the proper external excitation can be considered as a powerful control strategy for the stall. As an unsteady aerodynamic behavior of high angle of attack, the dynamic stall can be investigated from viewpoint of nonlinear dynamics, and there exists a rich variety of nonlinear phenomena, which are related to the lift enhancement and drag reduction.     

昆虫拍动翅的非定常变形对其气动力的影响

通过在动态变形网格上求解N-S方程的方法,研究了昆虫拍动翅的非定常变形对其气动力的影响．其中,拍动翅的扭转变形对气动力影响很小,拱形变形则会产生显著的影响,扭转和拱形组合变形的效果与拱形变形单独的效果基本相同．在6%拱形和20度扭转组合变形的情况下（此为对大量昆虫观察所得到的典型值）,相对于无变形平板翅,升力增加了10～20%,升阻比增加了约10%．翅膀的变形可增大最大升力系数;同时,可减小飞行的能耗,例如,对于做悬停飞行的熊蜂,其翅膀的动态变形（6%拱形和20度扭转组合变形）使其飞行中的能耗比无变形情况降低了约16%．     

Investigation of horizontal-axis wind turbine (HAWT) blade three-dimensional rotational e?ect based on ?eld experiments?

Field experiments are performed on a two-bladed 33 kW horizontal-axis wind turbine (HAWT). The pressures are measured with 191 pressure sensors positioned around the surfaces of seven spanwise section airfoils on one of the two blades. Three-dimensional (3D) and two-dimensional (2D) numerical simulations are performed, respectively, on the rotor and the seven airfoils of the blade. The results are compared with the experimental results of the pressure distribution on the seven airfoils and the lift coe?cients. The 3D rotational e?ect on the blade aerodynamic characteristics is then studied with a numerical approach. Finally, some conclusions are drawn as follows. From the tip to the root of the blade, the experimental di?erential pressure of the blade section airfoil increases at ?rst and then decreases gradually. The calculated 3D result of the pressure distribution on the blade surface is closer to that of the experiment than the 2D result. The 3D rotational e?ect has a signi?cant impact on the blade surface ?ow and the aerodynamic load, leading to an increase of the di?erential pressure on the airfoils and their lift coe?cient than that with the 2D one because of the stall delay. The in?uence of the 3D rotational e?ect on the wind turbine blade especially takes place on the sections with ?ow separation.     

Three-dimensional turbulent boundary layer on wind turbine blades

The momentum integral technique for predicting the boundary–layer growth in three–dimensional flow has been extended to include the entrainment equation as the closure model. Special attention has been devoted to those terms in the differential equations that change the boundary–layer structure from that of cvasi two–dimensional steady flow, at outboard locations, to a tree–dimensional flow pattern. It is concluded that the stall is delayed due to the boundary–layer reattachment at inboard sections in conjunction with the onset of a spanwise vortex like structure. (© 2008 WILEY-VCH Verlag GmbH & Co. KGaA, Weinheim)     

A numerical investigation on the dynamic stall of a vertical axis wind turbine

In the last years, for home user, the wind turbine with vertical axis (VAWT) began to be more attractive due benefits in exploitation. In terms of aerodynamics, when the wind speed approaches the speed of operation (low value of tip speed ratio -TSR) the blade airfoil exceeds the critical angle of incidence for static conditions. Angle of incidence varies quickly across blade and the blade works in dynamic stall condition. The goal of the present work is to investigate the two-dimensional dynamic stall phenomenon around the NACA 0012 airfoil at relatively low Reynolds. (© 2013 Wiley-VCH Verlag GmbH & Co. KGaA, Weinheim)