考虑法向压力梯度的三维旋转边界层计算

本文以量级分析为基础,建立了一般曲线坐标系上的三维旋转边界层方程。对旋转在边界层中的影响进行分析之后,提出了一个能够处理壁面法向压力梯度不为零问题的压力梯度迭代方法。在传统的Box法的基础上发展了一套完整的求解三维旋转边界层的方法和程序,并对螺旋面、压气机转子叶面以及圆柱面上的旋转边界层进行了计算,与他人的计算和实验的对比分析表明,该方法和程序是正确的,可用于求解任意几何物面上的三维旋转边界层。     

干涉条纹图处理的等值线窗口滤波和摄像测量在国防试验的应用

对图像进行滤波或称平滑是干涉条纹图像处理中的一项重要工作。一幅未经处理的原始图像或多或少存在着不同程度的噪声干扰,特别是散斑和Insar干涉条纹图,信噪比很低,难以处理。本文针对光测力学中光学干涉方法得到的条纹图,提出了一种新的滤波方法条纹等值线窗口滤波,并对这种滤波方法进行了研究讨论,提出了几种确定等值线窗口的不同方法。这种滤波方法根据干涉条纹图不同断面上灰度分布的不同特点,选择沿条纹走向的条纹等值线窗口进行滤波,在最大消除条纹图噪声的同时,也能保证对条纹损伤最小。摄像测量技术正在迅速发展和得到广泛应用,在国防试验和航天飞行任务中发挥着不可替代的作用。本文也介绍了作者近年来在该领域所做的应用研究,包括在火箭、导弹发射试验,冲击、碰撞等过程中的动态目标运动测量;针对航天航空和力学工程领域的视频图像实时分析;飞行器三维运动测量;基于投影条纹的物体三维形貌精密测量方法研究;以及对接航天器位置和姿态的实时测量。在这些应用中都实现了高精度测量。     

超音速/高超音速三维边界层的层流控制基金项目

根据可压缩黏性稳定性理论研究了壁面冷却和抽吸对超音速、高超音速三维边界层的层流控制作用.数值结果证明壁面冷却对第一模式起稳定作用,对第二模式有不稳定作用;壁面抽吸对第一、二模式都起稳定作用;直到Me＝7,导致绝热壁边界层转捩的始终是第一模式,Me≥6的冷却壁边界层则是第二模式对转捩起主导作用.壁面冷却能够推迟边界层转捩,但是和二维边界层相比壁面冷却对高速三维边界层的层流控制作用是很有限的.     

超音速／高超音速三维边界层的层流控制

根据可压缩黏性稳定性理论研究了壁面冷却和抽吸对超音速、高超音速三维边界层的层流控制作用。数值结果证明：壁面冷却对第一模式起稳定作用,对第二模式有不稳定作用;壁面抽吸对第一、二模式都起稳定作用;直到Me=7,导致绝热壁边界层转捩的始终是第一模式,Me≥6的冷却壁边界层则是第二模式对转捩起主导作用。壁面冷却能够推迟边界层转捩,但是和二维边界层相比壁面冷却对高速三维边界层的层流控制作用是很有限的。     

流对波边界层湍流运动的影响

采用大涡模拟方法和Smagorinsky亚格子模型，求解三维Navier-Stokes方程，研究了波流边界层中的湍流特性．将大涡模拟结果与相应的直接数值模拟结果和实验数据进行比较，吻合较好．获得了不同波雷诺数，不同波流比情况下的大涡模拟数据库，并由此分析了波流边界层中各种湍流统计量，如速度廓线、剪应力、湍流强度等的变化规律．     

大视场双目投影条纹方法中的相机参数标定与优化研究

投影条纹法具有高精度、高分辨的特点,且实验设备简单,对实验环境要求低,适宜于不同尺度的三维形貌测量。双目投影条纹法通常采用有标准参照物的相机标定方法获取相机参数,以实现物体表面三维形貌重建。然而,在大型结构的三维形貌测量中参照物的相对尺度较小,传统的基于重投影的相机标定方法在特征检测中引入的误差会被放大,从而影响三维表面形貌测量的稳定性和准确性。本文结合双目投影条纹成像原理,提出了一种适用于大面积形貌测量的投影条纹系统标定方法。该方法利用投影条纹控制点以及对极几何约束对张氏标定法结果进行优化,从而可以在大视场标定中保持较高的精度。实验表明,在标定板与测量物大小相当时,本文提出的标定方法与传统标定方法的测量结果基本一致;当标定板远小于待测物时,本文方法的测量精度和稳定性明显优于传统方法。     

三维高超音速球锥粘性绕流的计算

近二十年内,三维边界层方程的数值计算方法有了很大发展。由于求解三维边界层方程必须先得到无粘流场,或者二者进行迭代,其所需计算机的存储量及计算时间无疑是大量的。为此,发展和完善三维简化N-S方程(亦称广义边界层方程)的数值解法就日益显得重要起来。Rubin等及Helliwell等对抛物化的N-S方程(保留侧向扩散项)提     

对流传热边界层温度分布的激光干涉测量

本文介绍利用双镜干涉仪测量对流传热边界层中二维温度分布的方法。当冷空气流经热板模型时,附面层内的干涉条纹发生弯曲。根据条纹弯曲偏移量,由折射率与温度的关系,画出空气温度的二维分布图。整个过程由光学方法及微计算机全盘处理,是一种无接触测量方法。     

可压缩横流失稳及其控制

边界层流动转捩的预测与控制一直是流体力学研究中的一个重要问题. 三维边界层流动工程中十分常见, 而横流失稳是导致三维边界层流动转捩的主要原因. 本文综述了近些年来三维边界层失稳和转捩方面的研究概况. 从机理上讨论了横流扰动的感受性、首次失稳、二次失稳和转捩控制等方面的研究进展. 在数值计算方面, 简要概述了线性稳定性理论、非线性稳定性理论和直接数值模拟方法在横流失稳和转捩方面的应用.本文对横流失稳研究当前存在的问题进行了讨论, 对今后研究的发展趋势作了相应展望.     

三维不可压缩边界层分离流的反解法

本文提出了计算具有分离区的三维层流和湍流边界层的一种反解法。计算中采用了半正交曲线坐标系和涡粘性各向异性湍流模型。数值分析中采用了变换域技术和 Keller分块差分格式。用本文方法计算了一个三维边界层分离流实例,计算结果同实验数据吻合得很好。     

Growth of artificially induced disturbances in a supersonic boundary layer

This work proposes a method of inducing artificial disturbances of adjustable amplitude in a supersonic boundary layer. Using the proposed method, an experimental study is made of the development of a three-dimensional wave packet of low intensity at a frequency of 20 kHz in the boundary layer of a flat plate at Mach number M = 2.0. The Fourier components of the wave packet are determined. The data obtained are compared with the results of calculating the linear stability of the supersonic boundary layer in a plane-parallel flow approximation.Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 5, pp. 37–43, September–October, 1984.     

Effects of T-S wave amplitude on the control of boundary layer transition bystreaks

The effects of streaks on boundary layer transition depend on the initial amplitude of T-S waves introducedto excite the transition. This problem was studied in a flat-plate boundary layer in water tunnel byusing hydrogen bubble method. Three T-S wave initial amplitudes were tested. The results show thatboth narrow and wide-spacing streaks depress the transition excited by T-S waves with lower initialamplitude. However, when transition is excited by T-S waves of higher initial amplitude, thenarrow-spacing streaks depress the transition, while the wide-spacing streaks promote thetransition. Further the underlying mechanisms were also analyzed.     

Amplitude modulation and its relation to streamwise convection velocity

The paper is devoted to show the relation between the amplitude modulation and the convection velocity in a turbulent boundary layer. The analysis has been performed based upon velocity profiles measured with the hot-wire technique in a turbulent boundary layer with pressure gradient corresponding to turbomachinery conditions. The VITA detection method of small-scale structures was used in order to show the impact of the pressure gradient on phase averaged time-traces changes in the aspect of amplitude modulation. The physical significance of the large scales influence on the small scales, formerly known as the amplitude modulation, has been elucidated. It was demonstrated that the measure of amplitude modulation can be used as an indicator of the convection velocity of coherent structures. The convection velocity profile can be described in the inner region using the amplitude modulation term when the proper scale is applied. The convection velocity prediction in favourable and adverse pressure gradients shows that t the strongest impact of the pressure gradient occurs in the buffer layer. The stronger increase occurs in the buffer layer. It was also found that the skewness factor of phase-averaged VITA waveforms, is very similar in shape with the cross-product term of the streamwise skewness factor, which quantifies amplitude modulation. It indicates that the well-known modification of quadrant events in pressure gradient flows is a result of the amplitude modulation phenomenon.     

Development of three-dimensional disturbances in a boundary layer

In the region of transition from a two-dimensional laminar boundary layer to a turbulent one, three-dimensional flow occurs [1–3]. It has been proposed that this flow is formed as the result of nonlinear interaction of two-dimensional and three-dimensional disturbances predicted by linear hydrodynamic stability theory. Using many simplifications, [4, 5] performed a calculation of this interaction for a free boundary layer and a boundary layer on a wall with a very coarse approximation of the velocity profile. The results showed some argreement with experiment. On the other hand, it is known that disturbances of the Tollmin—Schlichting wave type can be observed at sufficiently high amplitude. This present study will use the method of successive linearization to calculate the primary two- and three-dimensional disturbances, and also the average secondary flow occurring because of nonlinear interaction of the primary disturbances. The method of calculation used is close to that of [4, 5], the disturbance parameters being calculated on the basis of a Blazius velocity profile. A detailed comparison of results with experimental data [1] is made. It developed that at large disturbance amplitude the amplitude growth rate differs from that of linear theory, while the spatial distribution of disturbances agree s well with the distribution given by the natural functions and their nonlinear interaction. In calculating the secondary flow an experimental correction was made to the amplitude growth rate.     

Mach Wave Radiation by Mixing Layers. Part I: Analysis of the Sound Field

In Part I a wave packet model is used to show that a time-developing mixing layer produces a Mach wave pattern similar to the one produced by a spatial-developing mixing layer. However, this kind of similarity does not exist for the sound emitted by subsonic sound sources. A method to analyse temporal direct numerical simulation (DNS) results for the Mach wave pattern is then developed and demonstrated using numerical results of the wave-packet model. The method is applied to the temporal DNS results of a supersonic mixing layer undergoing transition to turbulence. Two dominant Mach waves are revealed. The first wave originates from about the time of the Λ-vortex structure dominance in the layer. The second wave appears just prior to the final breakdown of the layer to a fine-scale turbulence structure. The second wave shows a higher level of a finite-amplitude wave behaviour and a smaller-scale source structure than the first wave. Directivity plots and frequency spectra are provided and discussed. Received 5 August 1997 and accepted 6 April 1998     

A hybrid numerical approach to predict the vibrational responses of panels excited by a turbulent boundary layer

In this work, a hybrid numerical approach to predict the vibrational responses of planar structures excited by a turbulent boundary layer is presented. The approach combines an uncorrelated wall plane wave technique with the finite element method. The wall pressure field induced by a turbulent boundary layer is obtained as a set of uncorrelated wall pressure plane waves. The amplitude of these plane waves are determined from the cross spectrum density function of the wall pressure field given either by empirical models from literature or from experimental data. The response of the planar structure subject to a turbulent boundary layer excitation is then obtained from an ensemble average of the different realizations. The numerical technique is computationally efficient as it rapidly converges using a small number of realizations. To demonstrate the method, the vibrational responses of two panels with simply supported or clamped boundary conditions and excited by a turbulent flow are considered. In the case study comprising a plate with simply supported boundary conditions, an analytical solution is employed for verification of the method. For both cases studies, numerical results from the hybrid approach are compared with experimental data measured in two different anechoic wind tunnels.     

Effect of turbulence of external flow on the turbulent boundary layer at a plate

In [1, 2] turbulence of the external flow was taken into account by specifying the turbulent energy at the external boundary of the boundary layer on integrating the energy-balance equation for the turbulence. In [3] a special correction that allowed the turbulence of the external flow to be taken into account was introduced in determining the mixture path. In [4, 5] the turbulent energy calculated from the energy-balance equation of the turbulence was added to the energy induced by turbulence of the external flow, the energy distribution of the induced turbulence being specified using an empirically selected function. In [6, 7] a method of taking into account the effect of turbulence of the external flow on a layer of mixing and a jet was proposed. In the present work, this method is applied to the boundary layer at a plate.Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 3, pp. 26–31, May–June, 1977.     

Ligament formation in sheared liquid–gas layers

We perform numerical simulations of two-phase liquid–gas sheared layers, with the objective of studying atomization. The Navier–Stokes equations for two-dimensional incompressible flow are solved in a periodic domain. A volume-of-fluid method is used to track the interface. The density ratio is kept around 10. The calculations show good agreement with a fully viscous Orr–Sommerfeld linear theory over several orders of magnitude of interface growth. The nonlinear development shows the growth of finger-like structures, or ligaments, and the detachment of droplets. The effect of the Weber and Reynolds numbers, the boundary layer width and the initial perturbation amplitude are discussed through a number of typical cases. Inversion of the liquid boundary layer is shown to yield more readily ligaments bending upwards and is thus more likely to produce droplets.     

Receptivity of the Swept Wing Boundary Layer to a Steady Flow Inhomogeneity

The boundary layer on a plate with an inclined blunt leading edge is investigated for a free-stream flow with a small span-periodic velocity inhomogeneity. This flow simulates the penetration of the outer turbulence into the swept wing boundary layer. It is shown that the boundary layer perturbations generated by the inhomogeneity generally have a streamwise velocity component significantly greater than the initial inhomogeneity amplitude. The dependence of the perturbations on the distance from the leading edge and the spanwise inhomogeneity period is found. It is shown that the swept wing boundary layer is less sensitive to the perturbation type in question than the straight wing boundary layer.     

An adaptive enrichment algorithm for advection‐dominated problems

We are interested in developing a numerical framework well suited for advection–diffusion problems when the advection part is dominant. In that case, given Dirichlet type boundary condition, it is well known that a boundary layer develops. To resolve correctly this layer, standard methods consist in increasing the mesh resolution and possibly increasing the formal accuracy of the numerical method. In this paper, we follow another path: we do not seek to increase the formal accuracy of the scheme but, by a careful choice of finite element, to lower the mesh resolution in the layer. Indeed the finite element representation we choose is locally the sum of a standard one plus an enrichment. This paper proposes such a method and with several numerical examples, we show the potential of this approach. In particular, we show that the method is not very sensitive to the choice of the enrichment and develop an adaptive algorithm to automatically choose the enrichment functions.Copyright © 2012 John Wiley & Sons, Ltd.