抽吸激波管的性能分析与计算

为了减小由于反射激波和透射激波分叉引起的反射型激波风洞试验气体提前受到污染的现象,本文研究了一种新的具有抽吸的激波管流动,分析了抽吸缝的作用,给出了这种抽吸激波管性能参数的计算方法,同时还给出了反射激波与边界层相互作用引起的激波分叉的形状随抽吸量变化的计算公式。实验证实了边界层抽吸可以有效地减小激波与壁面边界层相互作用所产生的分离现象。计算与测量结果是一致的。     

激波诱导含灰气体边界层中的粒子分布

本文研究当激波沿着一个固体表面等速地穿越含灰气体运动时所诱导的层流边界层特性。考虑了作用在气体边界层中球形粒子的 Saffman 升力,建议了一种计算近壁区中弥散相密度剖面的方法,并给出了数值计算结果。本文结果表明:在激波后方存在着一个弯曲的薄层区域,其中的粒子密度可以比其波前原始值增加许多倍。这种粒子聚集效应对于工业中粉尘爆炸等实际问题具有重要意义。     

一个改进的电磁波传输激波管实验

在中国科学院力学研究所Φ800 mm高温低密度激波管上进行电磁波在等离子体中传输机理研究时,低密度和强激波条件下,由于气体解离和电离等非平衡过程,使得激波后2区宽度显著减小;同时由于边界层效应造成激波衰减和接触面加速,使得激波后2区长度进一步减小.这两个效应导致激波管2区实验观测时间减小,2区气体处于非平衡状态,增加了观察数据的不稳定性和数据分析的难度.本文提出在Φ800 mm高温低密度激波管中采用氩气(Ar)和空气(Air)混合气替代纯空气作为激波管实验介质气体.利用Ar不解离和难电离的特性,减小激波前后压缩比,从而增加激波后2区实验时间和气体长度.采用Langmuir静电探针和微波透射诊断技术测量激波后电子密度,同时利用探针测量激波后2区实验时间.结果显示,在Ar+Air混合气实验中,激波波后电子密度可达与纯Air同样的10~(13)cm~(-3)量级.在与纯Air相同的电子密度和碰撞频率条件下,采用95%Ar+5%Air和90%Ar+10%Air两种混合气,激波后2区实验时间和气体长度约为纯Air条件下的5～10倍,其中2区实验时间为300～800μs,2区气体长度1～1.5 m.在Φ800 mm激波管中采用Ar+Air介质气体进行电磁波传输实验,获得了比在纯Air介质中与理论预测更一致的结果.     

管道凸起激波/湍流边界层干扰的数值模拟

采用基于部分平均的湍流方程组,模拟了管道凸起流动中两种不同强度的激波-湍流边界层干扰现象,对流场的时均参数与实验值进行了比较,计算得到的壁面压力分布、摩阻系数分布、边界层厚度和速度型与实验值比较吻合很好.结果表明基于部分平均的湍流方程组既能够准确模拟小分离的激波/湍流边界层干扰流动又能够准确模拟大分离的激波/湍流边界层干扰流动,较好地预测了典型的λ激波结构.     

触摸高温气体动力学

回顾了高温气体动力学与高超声速科技相关的一些重要研究进展,探讨几个具有基础性研究意义的方向：即高超声速流动模拟;高温气体热化学反应机制;高超声速流动滞止区预测;高超声速边界层转捩和激波/激波相互作用诱导的气动热问题．这些研究方向与高温气体效应和强激波密切相关,对高超声速科技关键技术的突破起着重要作用．     

一个改进的电磁波传输激波管实验

在中国科学院力学研究所$\varPhi $ 800 mm高温低密度激波管上进行电磁波在等离子体中传输机理研究时,低密度和强激波条件下,由于气体解离和电离等非平衡过程,使得激波后2区宽度显著减小;同时由于边界层效应造成激波衰减和接触面加速,使得激波后2区长度进一步减小.这两个效应导致激波管2区实验观测 时间减小,2区气体处于非平衡状态,增加了观察数据的不稳定性和数据分析的难度.本文提出在$\varPhi 800 $ mm高温低密度激波 管中采用氩气(Ar)和空气(Air)混合气替代纯空气作为激波管实验介质气体.利用Ar不解离和难电离的特性,减小激波前后压缩比,从而 增加激波后2区实验时间和气体长度. 采用Langmuir 静电探针和微波透射诊断技术测量激波后电子密度,同时利用探针测量激波后2区实验时间.结果显示,在Ar+Air混合气实验中,激波波后电子密度可达与纯Air同样的10$^{13}$cm$^{ - 3}$量级.在与纯Air相同的电子密度和碰撞频率条件下,采用95%Ar+5%Air和90%Ar+10%Air两种混合气,激波后2区实验时间和气体长度约为纯Air条件下的5$\sim $10倍,其中2区实验时间为300$\sim $800 $\mu$s,2区气体长度1$\sim $1.5 m.在$\varPhi $800 mm激波管中采用Ar+Air介质气体进行电磁波传输实验,获得了比在纯Air介质中与理论预测更一致的结果.      

侧压式道气道流场特性研究

应用表面油流和压力测量技术,结合数值模拟方法研究了超燃冲压发动机侧压式进气道无支板和有支板两种典型工况的基本流动特性.结果表明:由侧壁诱发的后掠激波与底板边界层相互作用,形成一对逆向旋转的漩涡,该漩涡在下游不断发展并偏离底板,在出口截面形成一个低马赫数低总压区;支板的引入增加了压缩率,但同时导致底板与侧壁边界层严重分离,使进气道性能偏离设计工况.     

在超声速流动中激波与边界层的干扰特性

激波与物面边界层的干扰涉及可压缩流动的稳定性、转捩、分离等问题,直接影响到飞行器的阻力、表面热防护和飞行性能等工程技术问题。首先总结了前人对于激波与边界层的干扰所做的工作,之后重点研究和对比分析了超声速与跨声速流动中,正激波、斜激波以及头部激波对于飞行器层流和湍流边界层的干扰影响。激波强度的不同对边界层干扰作用不同,在强干扰情况下将会引起边界层分离和翼型失速。     

INTERFERENCE OF SHOCK AND BOUNDARY LAYER IN SUPERSONIC FLOW

激波与物面边界层的干扰涉及可压缩流动的稳定性、转捩、分离等问题,直接影响到飞行器的阻力、表面热防护和飞行性能等工程技术问题。首先总结了前人对于激波与边界层的干扰所做的工作,之后重点研究和对比分析了超声速与跨声速流动中,正激波、斜激波以及头部激波对于飞行器层流和湍流边界层的干扰影响。激波强度的不同对边界层干扰作用不同,在强干扰情况下将会引起边界层分离和翼型失速。     

轴对称管口激波绕射诱导的复杂两相流动的数值分析

基于稀颗粒群假定下的双流体简化模型,采用具有高精度、高分辨率的数值方法,研究了粉尘气体中轴对称管口激波绕射诱导的复杂两相流动。得到非平衡两相流动不同于纯气体流动的一些基本物理特征,以及粒子物性参数改变对这些特性的影响。     

Boundary layer flows behind constant speed shock waves moving into a dusty gas

Laminar boundary layer flows behind constant speed shock waves moving into a dusty gas are analyzed numerically. The basic equations of two-phase flows are derived in shock fixed coordinates and solved by an implicit finite-difference method for the side wall boundary layer in a dusty gas shock tube. The development of the boundary layer and resulting velocity and temperature profiles, respectively, for the gas and particles are given from the shock front to far downstream. The effects of diaphragm pressure ratio, mass loading ratio of particles and particle size upon the flow properties are discussed in detail.This article was processed using Springer-Verlag T_EX Shock Waves macro package 1990.     

Numerical Simulation of the 3D Laminar Viscous Flow on a Horizontal-axis Wind Turbine Blade

The aim of this paper is to describe the methodology followed in order to determine the viscous effects of a uniform wind on the blades of small horizontal-axis wind turbines that rotate at a constant angular speed. The numerical calculation of the development of the three-dimensional boundary layer on the surface of the blades is carried out under laminar conditions and considering flow rotation, airfoil curvature and blade twist effects. The adopted geometry for the twisted blades is given by cambered thin blade sections conformed by circular are airfoils with constant chords. The blade is working under stationary conditions at a given tip speed ratio, so that an extensive laminar boundary layer without flow separation is expected. The boundary layer growth is determined on a non-orthogonal curvilinear coordinate system related to the geometry of the blade surface. Since the thickness of the boundary layer grows from the leading edge of the blade and also from the tip to the blade root, a domain transformation is proposed in order to solve the discretized equations in a regular computational 3D domain. The non-linear system of partial differential coupled equations that governs the boundary layer development is numerically solved applying a finite difference technique using the Krause zig-zag scheme. The resulting coupled equations of motion are linearized, leading to a tridiagonal system of equations that is iteratively solved for the velocity components inside the viscous layer applying the Thomas algorithm, procedure that allows the subsequent numerical determination of the shear stress distribution on the blade surface.     

The new solution for the axially symmetrical laminar boundary layer equations between two parallel sherical surfaces

The transformations, which are similar to Mangler’s transformations, are given in this paper. They change the entrance region flow of axially symmetrical laminar boundary layer between two parallel spherical surfaces into the flow of two-dimensional boundary layer, and simplify the problems. The simplified equations can be solved by the two-dimensional boundary layer theory and numerical methods. Therefore, a new way is opened up to solve the diffusive laminar flow in the entrance region between two parallel spherical surfaces.     

THE NEW SOLUTION FOR THE AXIALLY SYMMETRICAL LAMINAR BOUNDARY LAYER EQUATIONS BETWEEN TWO PARALLEL SPHERICAL SURFACES

The transformations, which are similar to Mangler's transformations, are given in this paper. They change the entrance region flow of axially symmetrical laminar boundary layer between two parallel spherical surfaces into the flow of two-dimensional boundary layer, and simplify the problems. The simplified equattons can be solved by the two-dimensional boundary layer theory and numerical methods. Therefore, a new way is opened up to solve the diffusive laminar fiow in the entrance region between two parallel spherical surfaces.     

Numerical Investigation of Multi-Jet Channel Flows

The results of a numerical simulation of the three-dimensional outflow of a system of circular supersonic turbulent jets into a cocurrent supersonic (or subsonic) air flow in a partially bounded region are given. Solutions are obtained by the splitting method using a matrix sweep of the parabolized Navier-Stokes equations. Assuming that the flow is nonseparated in the boundary layer, features of the three-dimensional structure of the jet system are investigated as functions of the pressure ratio number and the jet and cocurrent flow Mach numbers.     

The new solutions for two kinds of axially symmetrical laminar boundary layer equations

The transformations, which are similar to Mangier's transformation, are given in this paper, and make the two kinds of entrance region flow of axially symmetrical laminar boundary layer in internal way into the flow of two-dimensional boundary layer, and simplify the proboems. The simplified equations can be solved by the 2-D boundary layer theory. Therefore, a new way is opened up to solve the axially symmetrical flow in the entrance region of internal way.Project Supported by the Scientific Fund of Chinese Academy of Science.     

含尘离心风机中边界层对叶轮侵蚀的影响

本文采用二维可压缩紊流边界层计算模型,计算了离心风机内考虑边界层影响后的粒子轨迹和粒子与叶片表面的碰撞角、碰撞速度、磨损率沿叶片(相对弧长)的变化规律,计算结果表明:对于小直径的粒子,无粘流动假设是不合适的,计及边界层的影响,对于准确预测风机内的粒子轨迹和磨损是必不可少的。     

The Absolute Instability of Joukowski-Type Airfoils

In this paper an investigation is undertaken to explore the nature of the flow in the vicinity of the trailing edge of Joukowski-type airfoil configurations. Making use of the asymptotic interactive boundary layer theory, the basic flow profiles in the attached and detached flow regions are computed numerically through integrating the interactive boundary layer equations governing the flow motion for sufficiently large Reynolds numbers. Employing a Spectral Chebyshev collocation numerical integration scheme, boundary layer features corresponding to a number of thickness-to-chord ratio parameter cases are produced. The analysis carried out over the interaction region of the trailing edge shows that flow separation always takes place beyond certain critical value of the thickness-to-chord ratio parameter under the action of a self-induced pressure gradient. In addition, reversed flow regions of a sufficiently large size are found to be absolutely unstable, within the framework of linear spatio-temporal stability analysis in combination with the Briggs--Bers branch point criterion. Received 10 January 2001 and accepted 15 August 2001     

大型低速二元风洞侧壁边界层控制及对单段翼型实验结果的影响

本文简述了ＮＦ－３风洞二元实验段侧壁边界层吹除控制系统及具有吹气的模型实验方法，给出了不同吹气系数对风洞边界层的控制效果以及对相对厚度为７％的单段翼型实验结果的影响。初步实验研究结果表明，该控制系统能有效地改善风洞侧壁边界层的流动状态，减小侧壁干扰，改善翼型实验中的二元流动特性     

海岸城市上空热力内边界层的基本特征

海岸热力内边界层内大气在热力驱动下产生垂向对流运动,对海岸带的大气运动规律产生深刻的影响.在海岸城市地区,受城市冠层复杂结构的影响,热力内边界层呈现诸多独特的性质.采用大涡模拟的方法,研究了海岸城市热力内边界层内的流动特征.将海岸城市建筑物拟形为一系列有序排列的立方体块,并基于浸入边界方法考虑其对大气流动的影响.和常见的区域尺度数值研究中将城市下垫面假设为均质属性平面的方法相比,模拟结果的精度明显提高,海岸热力内边界层内各种尺度的动力过程也能在一定程度上得以描述.模拟计算了海岸城市热力内边界层、中性海岸城市边界层和开阔的自然海岸热力内边界层共3种情况,对比研究了城市摩阻和海岸热力作用对海岸城市上空大气运动的影响.研究结果表明:在空间上,边界层中各紊流特征量均在街谷尺度呈现出有规律而非均匀分布的特点;在强度上,热力作用与城市构筑物的摩阻作用相互促进,使得紊流强度显著提升并大于两种作用线性叠加的结果.此外,还发现有城市冠层海岸的热力内边界层发展远快于相同热力条件下的自然海岸带,边界层的发展规律也有显著的不同.