Flows around two airfoils performing fling and subsequent translation and translation and subsequent clap

The aerodynamic forces and flow structures of two airfoils performing “fling and subsequent translation“ and “translation and subsequent clap“ are studied by numerically solving the Navier-Stokes equations in moving overset grids. These motions are relevant to the flight of very small insects. The Reynolds number, based on the airfoil chord length c and the translation velocity U, is 17. It is shown that: (1) For two airfoils performing fling and subsequent translation, a large lift is generated both in the fling phase and in the early part of the translation phase. During the fling phase,a pair of leading edge vortices of large strength is generated; the generation of the vortex pair in a short period results in a large time rate of change of fluid impulse, which explains the large lift in this period. During the early part of the translation, the two leading edge vortices move with the airfoils;the relative movement of the vortices also results in a large time rate of change of fluid impulse, which explains the large lift in this part of motion. (In the later part of the translation, the vorticity in the vortices is diffused and convected into the wake.) The time averaged lift coefficient is approximately 2.4 times as large as that of a single airfoil performing a similar motion. (2) For two airfoils performing translation and subsequent clap, a large lift is generated in the clap phase. During the clap, a pair of trailing edge vortices of large strength are generated; again, the generation of the vortex pair in a short period (which results in a large time rate of change of fluid impulse) is responsible for the large lift in this period. The time averaged lift coefficient is approximately 1.6 times as large as that of a single airfoil performing a similar motion. (3) When the initial distance between the airfoils (in the case of clap, the final distance between the airfoils) varies from 0.1 to 0.2c, the lift on an airfoil decreases only slightly but the torque decreases greatly. When the distance is about lc， the interference effects between the two airfoils become very small.     

一类带有铁磁材料参数的非线性涡流问题的A-φ有限元法

针对带有铁磁材料的非线性涡流问题,其非线性性通常体现在磁场强度和磁感应强度的关系上.本文提出了一种全离散的有限元A-φ格式,分别在时间和空间上采用向后欧拉公式以及节点有限元进行离散.首先,在合适的函数空间里给出时间上的半离散格式,通过考察其弱形式建立相应的适定性理论,并证明近似解收敛于弱解.其次,给出全离散格式并讨论其误差估计.最后,给出两个数值算例以验证理论结果.     

HL-2M 初始放电位形及波形设计

利用 EFIT 设计了可用于 HL-2M 初始放电的圆截面限制器位形以及偏滤器位形;设计了满足放电击 穿条件要求(零场区域平均杂散磁场应不超过 20G)的零场位形。综合分析放电过程伏秒数消耗及真空室涡流的影 响,使用 PF8 线圈电流补偿真空室涡流产生的杂散磁场,设计了等离子体电流 200kA 的限制器位形及偏滤器位形 的自洽的放电波形。将该放电波形作为放电调试的参考波形,成功实现了限制器位形的初始放电实验。      

用晶格玻尔兹曼方法研究颗粒在涡流中的运动

用晶格玻尔兹曼方法研究小颗粒在涡流中的运动.涡流由流经空腔的流体产生.用动量交换法和压力张量积分法计算颗粒在涡流中的运动轨迹、速度和角速度.最后用张量积分法计算两个不同半径的颗粒在涡流中的运动. 关键词： 晶格玻尔兹曼方法 涡流 颗粒     

基于反射与折射理论的电涡流检测探头阻抗解析模型

应用电磁波的反射与折射理论建立了多层导电结构电涡流检测探头阻抗解析模型.电涡流检测中空间电磁场可看作线圈激励场与涡流场的叠加,而涡流场是线圈激励场的反射与折射效应,因此应用线圈激励场的级数型解析解和电磁波的反射与折射理论推导了级数型探头阻抗解析解.最后,比较了推导的级数型与传统的积分型探头阻抗解析解的计算结果,并进行了实验验证.计算结果与实验结果基本吻合,表明推导的级数型探头阻抗解析解是正确的,且与积分解析解相比具有不需要确定积分上限、耗时少、计算精度容易控制等优点. 关键词： 电涡流检测 多层导电结构 反射与折射理论 探头阻抗     

Simulation of Dynamics in Two-Dimensional Vortex Systems in Random Media

Dynamics in two-dimensional vortex systems with random pinning centres is investigated using molecular dynamical simulations. The driving force and temperature dependences of vortex velocity are investigated. Below the critical depinning force Fc, a creep motion of vortex is found at low temperature. At forces slightly above Fc, a part of vortices flow in winding channels at zero temperature. In the vortex channel flow region, we observe the abnormal behaviour of vortex dynamics： the velocity is roughly independent of temperature or even decreases with temperature at low temperatures. A phase diagram that describes different dynamics of vortices is presented.     

Spark-generated bubble collapse near or inside a circular aperture and the ensuing vortex ring and droplet formation

This paper aims to study the oscillation of a sparkgenerated submerged bubble located near or inside a circular aperture made in a flat plate using high-speed visualization technique. In the case of a bubble oscillating near an aperture the initial free surface of the water was set at the bottom surface of the plate. The effects of aperture size and bubblefree surface distance on the bubble behavior as well as on the ensuing droplet dynamics are investigated. It was found that the direction of the bubble reentrant jet was towards the aperture or away from it respectively when the normalized aperture size was smaller or greater than a certain critical value. In addition, a toroidal vortex ring was observed to form, which rotated inwards as it moved away from the aperture. It was also found that if the bubble was incepted at a distance sufficiently away from a supercritical size aperture a single droplet could be produced. In the case of a bub- ble initiated in the middle of a circular aperture submerged just beneath the water free surface, the bubble was found to take the shape of an ellipsoid during its expansion. Then a reentrant jet was initiated and pierced the bubble from its top side.     

Large eddy simulation and spectrum analysis of flow around two square cylinders arranged side by side

Large eddy simulation cooperated with the second order full extension ETG ( Euler-Taylor-Galerkin ) finite element method was applied to simulate the flow around two square cylinders arranged side by side at a spacing ratio of 1.5. The second order full extension ETG finite element method was developed by Wang and He. By means of Taylor expansion of terms containing time derivative, time derivative is replaced by space derivative. The function of it is equal to introducing an artificial viscosity term. The streamlines of the flow at different moments were obtained. The time history of drag coefficient, lift coefficient and the streamwise velocity on the symmetrical points were presented. Furthermore, the symmetrical problem of the frequency spectrum of flow around two square cylinders arranged side by side were studied by using the spectral analysis technology. The data obtained at the initialstage are excluded in order to avoid the influence of initial condition on the results. The power spectrums of drag coefficient, lift coefficient, the streamwise velocity on the symmetrical points were analyzed respectively. The results show that although the time domain process of dynamic parameters is nonsymmetrical, the frequency domain process of them is symmetrical under the symmetrical boundary conditions.     

三维涡流场分析的A,φ-Ω法*

本文在分析了不同规范下三维涡流问题的场域方程、界面连续条件后指出:在涡流区采用矢量磁位A,标量电位φ及库仑规范.A=0,在非导电区采用标量磁位Ω的求解策略较为合理,并给出了这一方法(A,φ-Ω法)的全部场域方程、边界条件、界面连续条件和相应的泛函.     

电涡流传感器的力学特性及其应用

本文对文献〔1〕中提出的电涡流传感器所受电磁力这一问题进行了进一步的研究,得到了更好的结果,理论计算与实验结果之间有很好的一致性.这个结果可用于修正某些使用了电涡流传感器的灵敏装置的测量结果,同时也可能用作一种非接触式的微小电子砝码,或者作为一种有用的微小力的发生器,其特点为易于按任一给定方向安装。