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     

可压缩流边界层参数的工程计算方法

本文把边界层理论中的参考焓方法推广到具有压力梯度的二维和三维轴对称流动,得到了物面动量厚度和摩阻的计算公式.同时利用边界层理论的某些成果推导了边界层各种厚度之间的近似关系.所得公式计算方便,与目前流行的但只适用于特殊情况的公式和有关的实验数据的比较表明,本文的结果是满意的.     

圆形地下连续墙场地地震反应的简化计算方法

首先将水平地震荷载作用沿环向展开为傅立叶级数,利用沿圆周法向和切向两个方向的正交性,再将水平地震荷载转化为一致横向荷载组合,使三维求解问题转变为一系列旋转子午面上二维问题的叠加,进而提出圆形地下连续墙场地地震反应的简化计算方法。之后,采用等效线性化方法来考虑土体非线性性质,进一步将非线性地震反应问题转化为线性问题求解。...     

表面有吸吮的旋转圆盘上的层流边界层问题的新解法

本文用文献[3]的摄动法求解有吸吮的旋转圆盘上的层流边界层方程.传统地方法是把边界层方程中的非线性项按边界层的厚度平均.按照本文的方法得到的计算摩擦力矩系数的公式(4.4)十分简单、与传统方法得到的相应公式相比较,当吸吮参量甚大时,二者十分符合.     

MODELLING AND CALCULATION OF THE TURBULENT BOUNDARY LAYER ON A ROTATING CYLINDER SURFACE WITH STRONG SUCTION 1)

提出了湍流边界层的一种简单、快速计算方法, 用以求解强吸气作用下旋转圆筒表面边界层流动. 首先, 理论分析了同心圆筒间的旋转流体运动, 外筒静止、内筒旋转且为多孔吸气条件. 强吸气情况下旋转流动主要表现为内筒壁面附近的边界层流动, 基于这一事实得到了周向速度分布的解析表达式. 其次, 通过引入新参数扩展Cebeci-Smith代数湍流模型, 使其能考虑流线曲率、壁面吸气、低Reynolds数效应等因素. 针对这些因素的综合影响, 采用解析修正和经验参数对模型进行调整. 同时, 基于Reynolds应力湍流模型的仿真结果, 校准代数湍流模型中的经验参数. 最后, 给出基于广义Cebeci-Smith湍流模型的旋转壁面边界层流动的迭代算法, 该算法适用于需要特殊迭代过程的轴向及周向流动均匀情况. 计算了不同旋转速度和吸气强度组合工况下的边界层流动, 其周向速度和湍流强度分布与基于Reynolds应力湍流模型的计算结果非常接近. 并且表明, 当Reynolds应力湍流模型数值模拟预测内筒边界层为稳定层流时, 该方法也再现了相同初始条件下的层流边界层.     

强吸气旋转圆筒壁面湍流边界层建模及计算

提出了湍流边界层的一种简单、快速计算方法, 用以求解强吸气作用下旋转圆筒表面边界层流动. 首先, 理论分析了同心圆筒间的旋转流体运动, 外筒静止、内筒旋转且为多孔吸气条件. 强吸气情况下旋转流动主要表现为内筒壁面附近的边界层流动, 基于这一事实得到了周向速度分布的解析表达式. 其次, 通过引入新参数扩展Cebeci-Smith代数湍流模型, 使其能考虑流线曲率、壁面吸气、低Reynolds数效应等因素. 针对这些因素的综合影响, 采用解析修正和经验参数对模型进行调整. 同时, 基于Reynolds应力湍流模型的仿真结果, 校准代数湍流模型中的经验参数. 最后, 给出基于广义Cebeci-Smith湍流模型的旋转壁面边界层流动的迭代算法, 该算法适用于需要特殊迭代过程的轴向及周向流动均匀情况. 计算了不同旋转速度和吸气强度组合工况下的边界层流动, 其周向速度和湍流强度分布与基于Reynolds应力湍流模型的计算结果非常接近. 并且表明, 当Reynolds应力湍流模型数值模拟预测内筒边界层为稳定层流时, 该方法也再现了相同初始条件下的层流边界层.      

绕侧滑翼三维可压缩湍流边界层计算

本文从广义曲线坐标运动方程出发,以及根据Head的二维牵引理论(entrainment theory)模型导出沿侧滑翼法向翼剖面表面曲线的三维可压缩湍流边界层运动方程组。通过矩阵变换得到具有初值问题的常微分方程组的典型形式,用数值方法求解。 利用Thompson和MacDonaId关于侧滑翼前缘附着线(attachment linc)上的绕流计算结果作为求解微分方程组的初值。 本文方法可计算出边界层分离位置,各种边界层厚度,壁面摩擦应力,描绘出壁面流线与边界层边缘流线间的差异。 典型算例表明本文方法与实验结果符合得很好。     

大跨度斜拉桥的动力特性及其颤振临界风速的计算

基于有限单元法理论,确定了斜拉桥合乎其构造特点的窨计算模型,建立了斜拉桥的自由振动的三维运动方程,对斜拉桥的动力特性进行了求解和分析,在此基础上,建立了在气动荷载作用下斜拉桥的三维运动方程,提出了用于分析斜拉桥颤振临界状态的子空间复特征值方法,推导出计算颤动临界风速的理论公式,并编写了用于计算斜拉桥颤振频率的多振型参与双参数自动搜索的计算机程序。     

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。     

水泵叶片表面三维边界层计算

本文用有限差分法计算混流式可逆水力机械水泵工况叶片表面的三维边界层。水泵叶轮中主流区的三维势流由直接边界元法计算。对于叶片面附近的粘性流动。用三维半正交坐标系中的边界层方程表示。为了提高计算精度采用贴体坐标技术生成边界层区域的计算网格。并利用Cebeci等变换函数及Keller差分格式离散方程。用分块解法求解。计算叶轮叶片表面的压力分布与相应试验结果进行了对比。     

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 three-dimensional boundary layer on a rotating flat plate as influenced by the containing end-walls

Growth of the turbulent boundary layer over a flat plate rotating about an axis parallel to the leading edge is considered in which the axial length (or span) is contained between rotating radial end-plates (the hub and shroud, in effect, of a centrifugal impeller). The problem of the influence of the cross-flows in the boundary layers on the end-plates as they affect the blade boundary layer is considered. The latter is treated as a three-dimensional problem and the dependence of the solution on the boundary conditions is discussed. The integral equations of this boundary layer reduce to a pair of quasi-linear partial differential equations which are weakly elliptic, parabolic, or weakly hyperbolic according to the rotation number. When the equations are exactly parabolic and the boundary layers remain thin it is shown that the end-plate boundary layers can have no influence upon the blade boundary layer if the flow is initially radial; separation of the end-plate cross flows takes place in the corners.     

Universal equations of the laminar boundary layer on a rotating blade

The article discusses the problem of the motion of an incompressible liquid in a boundary layer on a blade rotating uniformly around an axis perpendicular to the swing of the blade. A parametric method is used to solve the problem, and three series of parameters are introduced, on which depend the characteristics of the boundary layer. A corresponding system of universal equations is set up, which is integrated over a broad range of change in the parameters. The results obtained permit investigating the principal laws governing flow in a boundary layer on a rotating blade. The effect of rotation on breakaway and other characteristics of the boundary layer is clarified.Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 2, pp. 84–93, March–April, 1971.     

Bound vortex boundary layer control with application to V/STOL airplanes

Effectiveness of the bound vortex boundary layer control is assessed with reference to airfoils modified with a leading edge rotating cylinder. Results of the test program and the numerical models suggest the following:

• The surface singularity method in conjunction with the boundary layer correction scheme is capable of predicting useful information concerning bound vortex boundary layer control. The predicted pressure distributions are in good agreement with experiment almost up to the point of complete separation from the the airfoil surface except near the trailing edge where more accurate results of the flow field would require the modelling of the separated flow region using the full Navier-Stokes equations.

• The concept of bound vortex boundary layer control appears to be quite promising. With cylinder rotation. the flow never separated completely from the upper surface. The higher rates of rotation promoted reattachment of the partially separated flow giving a significant improvement in the maximum lift and stall characteristics.     

Differential infrared thermography for boundary layer transition detection on pitching rotor blade models

Differential infrared thermography (DIT) was investigated and applied for the detection of unsteady boundary layer transition locations on a pitching airfoil and on a rotating blade under cyclic pitch. DIT is based on image intensity differences between two successively recorded infrared images. The images were recorded with a high framing rate infrared camera. A pitching NACA0012 airfoil served as the first test object. The recorded images were used in order to investigate and to further improve evaluation strategies for periodically moving boundary layer transition lines. The measurement results are compared with the results of unsteady CFD simulations based on the DLR-TAU code. DIT was then used for the first time for the optical measurement of unsteady transition locations on helicopter rotor blade models under cyclic pitch and rotation. Image de-rotation for tracking the blade was employed using a rotating mirror to increase exposure time without causing motion blur. The paper describes the challenges that occurred during the recording and evaluation of the data in detail. However, the results were found to be encouraging to further improve the method toward the measurement of unsteady boundary layer transition lines on helicopter rotor models in forward flight.     

Evaporation phenomenon past a rotating hydrocarbon droplet of ternary components

A numerical study of heat and mass transfer from an evaporating fuel droplet rotating around its vertical axis was performed in forced convection only on the side opposite to the flow. The flow was assumed to be laminar, and the droplet was assumed to maintain its spherical shape during its lifetime. Based on the abovementioned assumption, the conservation equations in a general curvilinear coordinate were solved numerically. The behavior of rotating droplet evaporation in the forced convection flow can be investigated by analyzing the effects of the rotation of the droplet on the evaporation process of multi-component hydrocarbons droplet. The droplet is simulated to behave as a hard sphere. The transfer equations are discretized using an implicit finite difference method. Thomas algorithm is used to solve the system of algebraic equations. Moreover, dimensionless parameters of heat and mass transfer phenomena around a rotating hydrocarbon droplet were determined. The thickness of the boundary layer is unknown for this model and therefore, it was determined in function of time. Additionally, the study concerns “Dgheim dimensionless number” which is the ratio of the rotation forces over the viscosity forces. Dgheim dimensionless number is correlated to Nusselt and Sherwood numbers for multi-component hydrocarbon droplets in evaporation by taking into account the effect of heat and mass Spalding, Prandtl and Schmidt numbers respectively. Also, correlations for Nusselt and Sherwood numbers in terms of Reynolds, Prandtl and Schmidt numbers are proposed. These correlations consider the rotation phenomenon and advance the variation of the thermophysical and transport properties in the vapor phase of multi-component blends.     

Stretching surface in rotating viscoelastic fluid

The boundary layer flow over a stretching surface in a rotating viscoelastic fluid is considered. By applying a similarity transformation, the governing partial differ- ential equations are converted into a system of nonlinear ordinary differential equations before being solved numerically by the Keller-box method. The effects of the viscoelastic and rotation parameters on the skin friction coefficients and the velocity profiles are thor- oughly examined. The analysis reveals that the skin friction coefficients and the velocity in the x-direction increase as the viscoelastic parameter and the rotation parameter in- crease. Moreover, the velocity in the y-direction decreases as the viscoelastic parameter and the rotation parameter increase.     

低压涡轮内部流动及其气动设计研究进展

随着高空无人飞行器研究的不断升温, 高空低雷诺数条件下动力装置的研究越来越受到人们的重视.结合近年来国内外相关领域的研究工作, 对低雷诺数低压涡轮内部复杂流动机理的研究进展进行了介绍, 包括低雷诺数情况下低压涡轮内部非定常流动的特点, 叶片边界层分离及转捩现象机理, 上游周期性尾迹与下游叶片边界层相互作用机理等. 在此基础上给出了适合低雷诺数条件的低压涡轮气动设计方法:尾迹通过与边界层的相互作用, 能够抑制分离, 进而减小叶型损失, 在气动设计中有效引入非定常效应可以大幅度提高低压涡轮的气动负荷或降低气动损失, 最终达到提高性能的目的;数值及实验结果验证了这种设计方法的有效性.      

Prediction of periodic boundary layers

A relatively simple, yet efficient and accurate finite difference method is developed for the solution of the unsteady boundary layer equations for both laminar and turbulent flows. The numerical procedure is subjected to rigorous validation tests in the laminar case, comparing its predictions with exact analytical solutions, asymptotic solutions, and/or experimental results. Calculations of periodic laminar boundary layers are performed from low to very high oscillation frequencies, for small and large amplitudes, for zero as well as adverse time-mean pressure gradients, and even in the presence of significant flow reversal. The numerical method is then applied to predict a relatively simple experimental periodic turbulent boundary layer, using two well-known quasi-steady closure models. The predictions are shown to be in good agreement with the measurements, thereby demonstrating the suitability of the present numerical scheme for handling periodic turbulent boundary layers. The method is thus a useful tool for the further development of turbulence models for more complex unsteady flows.