Direct numerical simulation of compressible turbulent flows

This paper reviews the authors＇ recent studies on compressible turbulence by using direct numerical simulation （DNS）,including DNS of isotropic（decaying） turbulence, turbulent mixing-layer,turbulent boundary-layer and shock/boundary-layer interaction.Turbulence statistics, compressibility effects,turbulent kinetic energy budget and coherent structures are studied based on the DNS data.The mechanism of sound source in turbulent flows is also analyzed. It shows that DNS is a powerful tool for the mechanistic study of compressible turbulence.     

用三分量热线探头测量平板湍流边界层

本文用三分量热线探头，同时测量了零压梯度平板湍流边界层三个方向的脉动速度分量；用数学信号处理技术研究了平板湍流边界层的统计特性，并对测量结构进行了讨论。     

扩散抛物化Navier-Stokes方程数值解法评述

20世纪60年代末期在边界层理论基础上发展起来的各种简化Navier-Stokes (N-S)方程(统称为扩散抛物化N-S方程)及其算法, 较为彻底地解决了无黏流及黏流的相互干扰问题, 并为高雷诺数大型复杂黏性流场的数值模拟开辟了新的途径. 本文将系统地评述这一领域的主要成果, 包括各种简化N-S模型的优缺点; 数学奇性及正则化方法; 代表性的数值解法以及最近几年的新进展.      

大气边界层内羽流扩散研究

主要研究了高架点源的污染,即``羽流扩散'. 由于大气边界层内的湍流运动,引 起污染物扩散的主要因素是湍流扩散, 研究湍流扩散有两种基本方法：统计理论和梯度理论. 采用拉格朗日粒子扩散模型 (Lagrangian particle dispersion model, LPDM)来评价羽流扩散的平均浓度,分别计算了表征扩散程度的3个参数：沿烟轴方向的 着地浓度、水平方向的羽流扩散宽度和垂直方向的羽流扩散宽度. 从计算结果和风洞实验的 数据对比来看,用该模式可以较好地模拟大气边界层内复杂气候条件下的羽流扩散.     

离心泵叶片边界层分离对水动力特性的影响

给出了离心泵叶片近壁表面流体粘性流动的分析方法,通过对叶片压力面边界层参数的计算和边界层分离的判断,确定分离型和流线型叶片型线,又通过对测试泵的性能对比试验,验证了叶片型线对水动力特性的影响,明确了这种影响主要体现在离心泵的水力效率、动力性能方面,并指出叶片形状的变化是导致其表面流体边界层分离点位置移动的主要原因,它决定了边界层是否分离,而过大的分离将使测试泵的性能下降,振动剧烈、噪声增大,并强调应重视边界层分析在叶片水力设计中的作用,同时给出了叶片型线水力设计的评价依据。所得结论对低比转速离心泵水动力特性的改善有参考价值。     

Multi-scale coherent structures in turbulent boundary layer detected by locally averaged velocity structure functions

Introduction Inearlyperiodofstudyofturbulentflow,itwasdeemedrandomanddisorderedmotionsof fluidparticles,sothecharacteristicsofturbulencewerestudiedbystatisticsaveragemethod. Kolmogorov[1]analyzedtherelativemotionoffluidparticlesinfullydeveloped(Reynolds numbertrendstoinfinity)isotropicandhomogeneousturbulentflow,onbasisofrandomfield theory,andpresentedtheconceptofstructurefunctions,whichdescribedtherelativevelocityof twofluidparticlesindistanceofl,toresearchthelawbetweenthemulti_orderstatistic…     

Analytical solutions for thermal forcing vortices in boundary layer and its applications

Using the Boussinesq approximation, the vortex in the boundary layer is assumed to be axisymmetrical and thermal-wind balanced system forced by diabatic heating and friction, and is solved as an initial-value problem of linearized vortex equation set in cylindrical coordinates. The impacts of thermal forcing on the flow field structure of vortex are analyzed. It is found that thermal forcing has significant impacts on the flow field structure, and the material representative forms of these impacts are closely related to the radial distribution of heating. The discussion for the analytical solutions for the vortex in the boundary layer can explain some main structures of the vortex over the Tibetan Plateau.     

Stability analysis and transition prediction of hypersonic boundary layer over a blunt cone with small nose bluntness at zero angle of attack

Stability and transition prediction of hypersonic boundary layer on a blunt cone with small nose bluntness at zero angle of attack was investigated. The nose radius of the cone is 0.5 mm; the cone half-angle is 5°, and the Mach number of the oncoming flow is 6. The base flow of the blunt cone was obtained by direct numerical simulation. The linear stability theory was applied for the analysis of the first mode and the second mode unstable waves under both isothermal and adiabatic wall condition, and eN method was used for the prediction of transition location. The N factor was tentatively taken as 10, as no experimentally confirmed value was available. It is found that the wall temperature condition has a great effect on the transition location. For adiabatic wall, transition would take place more rearward than those for isothermal wall. And despite that for high Mach number flows, the maximum amplification rate of the second mode wave is far bigger than the maximum amplification rate of the first mode wave, the transition location of the boundary layer with adiabatic wall is controlled by the growth of first mode unstable waves. The methods employed in this paper are expected to be also applicable to the transition prediction for the three dimensional boundary layers on cones with angle of attack.     

Verification of parabolized stability equations for its application to compressible boundary layers

Parabolized stability equations (PSE) were used to study the evolution of disturbances in compressible boundary layers.The results were compared with those ob- tained by direct numerical simulations (DNS),to check if the results from PSE method were reliable or not.The results of comparison showed that no matter for subsonic or supersonic boundary layers,results from both the PSE and DNS method agreed with each other reasonably well,and the agreement between temperatures was better than those between velocities.In addition,linear PSE was used to calculate the neutral curve for small amplitude disturbances in a supersonic boundary layer.Compared with those obtained by linear stability theory (LST),the situation was similar to those for incom- pressible boundary layer.     

压力梯度对边界层两相流动稳定性的影响

分析了有压力梯度的边界层两相流动稳定性,推导出类似于Saffman理论的修正的稳定性方程,数值计算采用高精度的谱方法。结果说明,压力梯度对边界层两相流动稳定性有显著的影响,顺压梯度增强流动稳定性,而逆压梯度则促进流动失稳。在不同的压力梯度和浓度下,Stokes数对流动稳定性的影响是一致的,存在一个临界Stokes数,小Stokes数促进流动失稳,而大Stokes数则提高临界雷诺数,抑制流动失稳的最佳Stokes数为10的量级。