Euler solution using adaptive Cartesian grid with a gridless boundary treatment

A quadtree-based adaptive Cartesian grid generator and flow solver were developed. The grid adaptation based on pressure or density gradient was performed and a gridless method based on the least-square fashion was used to treat the wall surface boundary condition, which is generally difficult to be handled for the common Cartesian grid. First, to validate the technique of grid adaptation, the benchmarks over a forward-facing step and double Mach reflection were computed. Second, the flows over the NACA 0012 airfoil and a two-element airfoil were calculated to validate the developed gridless method. The computational results indi- cate the developed method is reasonable for complex flows.     

Numerical investigation on the flowfield of ＂swallowtail＂ cavity for supersonic mixing enhancement

A ＂swallowtail＂ cavity for the supersonic combustor was proposed to serve as an efficient flame holder for scramjets by enhancing the mass exchange between the cavity and the main flow. A numerical study on the ＂swallow- tail＂ cavity was conducted by solving the three-dimensional Reynolds-averaged Navier-Stokes equations implemented with a k-e turbulence model in a multi-block mesh. Turbu- lence model and numerical algorithms were validated first, and then test cases were calculated to investigate into the mechanism of cavity flows. Numerical results demonstrated that the certain mass in the supersonic main flow was sucked into the cavity and moved spirally toward the combustor walls. After that, the flow went out of the cavity at its lateral end, and finally was efficiently mixed with the main flow. The comparison between the ＂swallowtail＂ cavity and the conventional one showed that the mass exchanged between the cavity and the main flow was enhanced by the lateral flow that was induced due to the pressure gradient inside the cavity and was driven by the three-dimensional vortex ring generated from the ＂swallowtail＂ cavity structure.     

高超声速激波风洞研究进展

回顾了高超声速激波风洞的研制与发展,并依据高超声速实验研究对地面实验模拟技术的要求,分别介绍了应用轻气体、自由活塞和爆轰驱动技术研制的主要激波风洞的性能、特点和存在问题.重点介绍了爆轰驱动高焓激波风洞的3种主要运行模式:反向、正向爆轰驱动与双爆轰驱动. 根据这些运行模式的工作原理,分析了应用这些驱动技术产生的高温、高压气源的特点,探讨了不同驱动技术可能影响激波风洞性能的关键问题与解决方法.目前发展的激波风洞已经能够用于开展马赫数3$\sim$30的高超声速流动的试验模拟研究,但是试验气流的品质还不能满足高超声速科技研究的需求.为了获得可靠的实验结果, 通过不断改进、完善、提高激波风洞的性能,尽可能复现高超声速飞行条件是今后主要的研究方向.      

壁流动中的转捩

对壁流动的不同实验结果做了对比,这些实验结果来自于流动显示、热膜测量以及PIV测量, 对比的同时,还总结了与此相应的理论方面的进展.这些进展是在对所选大约120篇文献中内容归纳提炼的基础上给出的.尽管实验中所使用的初始扰动条件不同,但所发现的流动结构几乎是完全一样的. 在对壁流动转捩的认识方面,认为下列所观察到的流动结构是最基本最重要的:在边界层和管流中被称为类孤子相干结构(SCS)的三维非线性涡包、$\Lambda$涡、二次涡环和涡环链.近期的实验中发现了这些结构形成和转捩的动力学过程,具体包括以下内容: (1) $\Lambda$ 涡和二次涡环间持续的相互作用过程.该过程决定了涡环链的产生方式, 总是从壁面区域周期性地形成,并进入到边界层的外部区域; (2)高频涡的生成,这是理解转捩和湍流边界层(以及其他流动)发展的关键问题之一.尽管已经提出了一些解释,但是二次涡环的实验发现将对此提供一个特别清晰的解释.(3)在所有湍流猝发中SCS所起的关键作用.这一点被看做是低雷诺数湍流边界层中湍流产生的关键机制.与猝发直接相关联的是低速条带. 基于SCS的动力学过程, 针对壁流动情况,可以比以前更清晰地解释低速条带的形成机制及其与流动结构的关系.在实验中所观察到的SCS和二次涡环,不仅能使我们重温壁面流动转捩中的经典故事, 同时还开辟一条新的途径,可以基于此建立壁面流动转捩可能具有的普适性的动力学过程.      

基于小型电磁动力驱动器的微流道混合控制研究

对于许多微流体应用系统来说,流体的混合是至关重要的.本文研究了基于电磁流体动力混合器的微流道主动混合控制方法,建立了该微流道混合系统的理论模型并进行了数值模拟.在交变Lorentz驱动下,流经混合器流道的流体及其分界面在混合器流道内往复运动,流体界面的反复折叠与流体局部流动使流体混合,流体的横向往复运动使流体分界面反复折叠从而使流体间的接触面积大大增加.对流体混合过程进行了讨论并给出了漉体混合程度评价方法.     

常气压辉光放电等离子体对边界层流动的影响

基于Shyy提出的常气压下均匀辉光放电等离子体与空气干扰的物理模型,通过求解电位势方程得到电场分布及作用于流体上的电场力.以NACA0015翼型低速绕流为对象,通过数值求解考虑等离子体作用的流体运动控制方程,研究等离子体位置和个数控制对翼型绕流分离的影响.位于分离点上游的等离子体能够有效地抑制流动分离,而在分离区的等离子体对流动影响很弱,这一结论同实验观察一致,并给出等离子体对翼型壁面压力和气动力影响的规律.     

Numerical investigations of asymmetric flow of a micropolar fluid between two porous disks

Numerical solution is presented for the two- dimensional flow of a micropolar fluid between two porous coaxial disks of different permeability for a range of Reynolds number Re （-300≤ Re 〈 0） and permeability parameter A （1.0≤A ≤2.0）. The main flow is superimposed by the injection at the surfaces of the two disks. Von Karman＇s similarity transformations are used to reduce the governing equations of motion to a set of non-linear coupled ordinary differential equations （ODEs） in dimensionless form. An algorithm based on the finite difference method is employed to solve these ODEs and Richardson＇s extrapolation is used to obtain higher order accuracy. The results indicate that the parameters Re and A have a strong influence on the velocity and microrotation profiles, shear stresses at the disks and the position of the viscous/shear layer. The micropolar material constants cl, c2, c3 have profound effect on microrotation as compared to their effect on streamwise and axial velocity profiles. The results of micropolar fluids are compared with the results for Newtonian fluids.     

手性流动相添加法拆分酮康唑外消旋体

采用C18反相色谱柱,利用在流动相中加入手性选择剂的方法实现酮康唑对映体的拆分。研究了手性选择剂的种类及浓度、流动相pH值、甲醇比例和柱温等因素对酮康唑手性分离的影响,结果表明磺丁基-β-环糊精可以使酮康唑对映体完全分离,最后选择的流动相组成为甲醇-0.02 mol/L磷酸二氢钠(体积比为60∶40,含0.02%三乙胺和1.0 mmol/L磺丁基-β-环糊精,用稀磷酸调节pH值到3.00)。酮康唑对映体在6 min内得到基线分离,分离度为2.05。方法简便,分离效果好,对酮康唑对映体的拆分具有应用价值。     

过渡区气体微尺度流动的格子Boltzmann模拟

采用格子Boltzmann方法(LBM)对过渡区内的微尺度气体流动进行了模拟研究. 在已有滑移区微流动LBM模型中引入Knudsen层速度修正,选取合适的修正函数表达式并依据动理论确定了可调参数的合理取值. 在边界条件的处理格式上,采用了适合过渡区模拟的高阶滑移边界的替代格式来捕捉过渡区微流动的滑移速度,避免了直接求解高阶速度导数项的数值困难. 通过对两类不同的微流动进行模拟的结果表明:与数值解吻合得较好,尤其是对Kn>0.5微流动滑移速度的预测,与已有LBM的模拟结果相比有明显的提高.      

用于板料成形反向模拟的特殊应力更新算法

提出了一种改进的反向模拟法,以最终构型为研究对象,采用Euler坐标系,基于虚功原理获得有限元列式. 改进的反向模拟法采用了一种基于塑性流动理论的本构方程,可以充分考虑应变历史对塑性变形的影响. 为了避免流动理论应力更新算法过程中关于未知量\Delta\lambda 的非线性方程的求解,引入等效应力思想,无需Newton-Raphson迭代直接计算未知量\Delta \lambda . 盒形件的拉深实例中,传统的基于塑性形变本构方程的反向模拟法和改进的基于塑性流动本构方程的反向模拟法计算结果,分别与基于增量有限元法的正向数值模拟求解器LS-DYNA计算结果进行对比. 通过获得的坯料轮廓、成形极限图、等效应变分布、计算效率等的比较,验证了所提出的基于塑性流动理论本构模型的应力更新算法的有效性.