Effect of vertical large eddy breakup devices on the drag of a flat plate

Experiments are performed to study the possibility of decreasing the net drag of a flat plate with the use of streamwise-oriented vertical elements mounted normal to the surface in an incompressible equilibrium turbulent boundary layer. The Reynolds number based on the boundary-layer momentum thickness in the section where the vertical elements are placed is 820. It is demonstrated that vertical large eddy breakup elements with the geometry used do not reduce the drag of a flat plate in the major part of the range of Reynolds numbers Re _x examined. It is only at extremely low values of Re _x that a certain gain in the net drag is reached, as compared with the value for a non-modified flow.     

Turbulent boundary layer on a body of revolution with periodic blowing/suction

The effect of periodic blowing/suction on characteristics of a turbulent boundary layer formed on an axisymmetric body of revolution in a nominally gradientless incompressible flow is studied experimentally. The Reynolds number based on the momentum thickness at the location of an annular slot for blowing/suction is 1176. The dimensionless slot width in the wall units is 68. It is demonstrated that blowing/suction aimed at controlling the boundary-layer flow is a fairly effective method for controlling the near-wall turbulence structure and ensures a certain gain in friction drag over the initial configuration (the maximum gain reaches 25–30 %).     

基于蚯蚓背孔射流的仿生射流表面减阻性能研究

为了减小流体对固体壁面的阻力, 基于蚯蚓生物学特征, 对蚯蚓背孔射流特性进行分析, 建立仿蚯蚓背孔射流的仿生射流表面计算模型, 采用SST k-ω 湍流模型对仿生射流表面的减阻特性进行数值模拟, 同时对数值模拟结果进行实验验证, 并以此研究了仿蚯蚓背孔射流表面的减阻机理.结果表明, 在一定条件下, 仿蚯蚓背孔射流的仿生射流表面具有较好的减阻效果; 在同一射流方向角下, 随着射流速度的增加, 减阻率逐渐增大; 在同一射流速度下, 随着射流方向角的增加, 减阻率呈先减小后增大的变化趋势; 数值模拟与实验均在射流速度为1 m·s^-1、射流方向角为-30°时达到最大, 分别为8.69%, 7.86%; 射流表面改变了原有光滑壁面的边界层结构, 对壁面边界层进行了有效的控制, 减小了壁面的剪应力, 降低了壁面边界层的速度.     

电磁力控制湍流边界层分离圆柱绕流场特性数值分析

在亚临界区高雷诺数Re=1.4×105下,采用脱体涡模拟结合湍流分离的方法对弱电解质中电磁力作用下湍流边界层分离圆柱绕流场及其升(阻)力特性进行了数值模拟和分析.结果表明,电磁力可以提高圆柱体湍流边界层内的流体动能,延缓圆柱体湍流边界层的流动分离,减弱圆柱体湍流绕流场中在流向和展向上大尺度漩涡的强度,减小圆柱体阻力时均值及其升力脉动幅值.当电磁力作用参数大于某个临界值后,湍流边界层流动分离消失,在圆柱体尾部产生射流现象,从而电磁力对圆柱体产生净推力作用,出现负阻力现象,而且升力脉动幅值接近于零,出现圆柱体升力消失现象.     

Effectiveness of blowing for improving the high-speed trains aerodynamics

The promising method of drag reduction with the use of micro-blowing through the streamlined surface has been proposed for its use to the external surface of high-speed train. The advantages of high-speed train as an object of micro-blowing application are introduced. The corresponding RANS-based mathematical model is elaborated, and the computations of the external flow around a long train body are performed. Predictions of the turbulent boundary layer over penetrable surface with different modes of micro-blowing have been presented and analyzed. The developed modifications of mathematical model of turbulence have been used to take into account the micro-blowing influence in the inner region of turbulent boundary layer. The obtained results of parametric analysis of drag reduction depending on the area of permeable sections, intensity of micro-blowing, and high-speed train length have been analyzed. In particular, the dependence between drag reduction effect and length of train body with realized micro-blowing as well as its intensity is established. Realization of micro-blowing with blowing velocity just 0.25 % of train speed (V = 100 m/s) on the 70 % of the streamlined surface area for just one train carriage (L = 25 m) allows one to reduce the aerodynamic drag (including the most actual friction and head-tail pressure components) of the whole train (L = 200 m) by about 5.25 %, so in case of micro-blowing realization on all its 8 carriages, the train’s aerodynamic drag can be reduced approximately by 42 %.     

Experimental investigation on underwater drag reduction using partial cavitation

For underwater drag reduction, one promising idea is to form a continuous gas or discrete bubbly layer at the submerged surface. Owing to the lower viscosity of gas than of water, this could considerably reduce underwater drag by achieving slippage at the liquid–gas interface. This paper presents an experimental investigation on underwater drag reduction using partial cavitation. Dense hydrophobic micro-grooved structures sustain gas in the valleys, which can be considered as defects that weaken the strength of the water body. Therefore, partial cavities are easily formed at lower flow speeds, and the dense cavities connect to form a lubricating gas layer at the solid–liquid interface. The results indicate that the proposed method achieves drag reduction without any additional energy or gas-providing devices, which should stimulate the development of underwater vehicles.     

On the vertical large eddy breakup device capability to decrease the turbulent drag

The possibility of decreasing the turbulent friction with the use of streamwise-aligned vertical large eddy breakup devices installed normal to the surface of a flat plate in an incompressible equilibrium turbulent boundary layer with a nominally gradientless flow past this plate is studied experimentally. The Reynolds number based on the boundary-layer momentum thickness is 1099 in the cross section where these vertical devices are mounted. It is shown that elements of this geometry are effective tools for modification of the turbulent boundary layer from the viewpoint of both the gain in friction drag and the suppression of turbulent fluctuations of velocity and, hence, can be considered as one of the most important factors of controlling the structure of the near-wall turbulence in the flow past a flat surface.     

仿生射流孔形状减阻性能数值模拟及实验研究

针对横流中的侧向射流能够减小仿生射流表面摩擦阻力问题, 建立仿生射流表面模型, 利用SST k-ω湍模型对不同射流孔形状的仿生射流表面模型进行数值模拟, 并对数值模拟结果进行了实验验证. 结果表明: 当射流孔的流向长度和展向长度不变时, 3号模型的折线形射流孔减阻效果最好; 将折线形射流孔简化为圆弧形, 当r=3–5 mm时, 减阻率随着射流速度的增大而增大, 当r=4 mm时减阻效果最好, 最大减阻率为9.51%. 减阻原因: 通过射流孔向横向主流场中注入射流流体, 改变了射流表面附近边界层的流场结构, 使得边界层黏性底层厚度增加, 垂直于射流表面的法向速度梯度减小, 从而减小了壁面剪应力; 低速的射流流体被封锁在边界层内, 降低了高速流体对壁面的扫掠, 达到了减阻目的.     

Drag force reduction on an airfoil via glow discharge plasma-based control

Glow discharge plasma on a solid surface will result in a body force which modifies the pressure distribution along the flow boundary layer, and consequently re-attaches the separated flows for reduction of a hydrodynamic drag force. In this paper, we investigate the discharge performance of various plasma-actuated electrodes in terms of their arrangements and structures. The resulting optimal configuration for the electrode separation distance was used to develop a flexible actuated panel to be mounted onto a NACA 0015 airfoil. Both uniphase and eight-phase power inputs were used to examine its drag reduction performance at various attack angles and flow velocities. Numerical calculations were also performed by including an electrostatic body force in the hydrodynamic equation. Good agreement were found between the numerical and experiment results.     

Bubbly turbulent drag reduction is a boundary layer effect

In turbulent Taylor-Couette flow, the injection of bubbles reduces the overall drag. On the other hand, rough walls enhance the overall drag. In this work, we inject bubbles into turbulent Taylor-Couette flow with rough walls (with a Reynolds number up to 4 x 10(5), finding an enhancement of the dimensionless drag as compared to the case without bubbles. The dimensional drag is unchanged. As in the rough-wall case no smooth boundary layers can develop, the results demonstrate that bubbly drag reduction is a pure boundary layer effect.     

Mean velocity behaviour in the near wake of long slender cylinder with a sharp trailing edge at a high Reynolds number

A simple eddy viscosity model is applied to the governing equations to establish the behaviour of the mean velocity in the turbulent axisymmetric near wake. The near wake develops from a long slender cylinder which is kept parallel to the flow and is developing under zero streamwise pressure gradient. The upstream turbulent boundary layer on the body of revolution is fully developed. In the inner layer of the flow downstream of the trailing edge, the turbulent inner layer of the upstream boundary layer grows into the initial logarithmic layer, and as a consequence, the centreline velocity in the near wake is shown to increase logarithmically with streamwise distances for large streamwise distances. The analysis further leads to two regions of the near wake flow (the inner near wake and the outer near wake), similar to that of a fully developed turbulent boundary layer, for which the governing equations have been derived. The matching between these two regions leads to a logarithmic variation in the normal direction. Also shown is the variation of the square of the wake width which varies logarithmically with streamwise distance in the near wake. These features are validated by comparison with available experimental data.     

Modelling of turbulent boundary layers on the body of revolution in the presence of large eddy breakup devices

A novel approach was proposed to developing a combined algebraic-differential model of turbulent viscosity, which was then used to modify the traditional method for calculating turbulent boundary layers on bodies of revolution immersed in an incompressible flow. Ample experimental data were invoked to test the developed model through prediction of features inherent in turbulent boundary layers on the body of revolution in the presence of Large Eddy BreakUp (LEBU) devices installed in the vicinity of the streamlined surface. Within the developed approach, we showed it possible to calculate the evolution of local governing characteristics of turbulent flow in a broad range of LEBU parameters.     

Drag reduction by compliant coatings made of a homogeneous material

The possibility of drag reduction due to compliant coatings of viscoelastic silicone rubbers has been tested experimentally. For this purpose, a series of single-layer coatings of various thicknesses was made of a homogeneous material. The experiments were carried out in a high-speed cavitation tunnel of Pusan National University. Dynamic viscoelastic properties of coating materials were carefully measured. The range of flow rates and coating thicknesses was calculated assuming that the coatings can interact intensively with the dynamic structures of the turbulent boundary layer only in the region of frequencies of their maximum compliance. The predicted range of coating parameters and flow velocities, in which the coatings reduce drag, is compared with experimental data.     

翼型绕流的洛伦兹力控制机理

在翼型上翼面壁面附近流场中形成的流向洛伦兹力,可提升翼型的升力减小阻力,然而制约其推广应用的主要瓶颈是极为低下的控制效率,为提高洛伦兹力的控制效率,需研究其控制机理.以翼型绕流的洛伦兹力控制为例,利用双时间步Roe格式及水槽对其进行数值及实验研究.结果表明:洛伦兹力的控制效果随着来流速度的增加而下降,升力增幅和阻力减幅与来流速度大小呈反比关系,但升力增加和阻力减小的规律不变,都是升力先急剧增加随后缓慢增加,而阻力先急剧减小然后再缓慢增加,基本原因为升力和阻力先受洛伦兹力推力的影响而分别增加和减小,随后洛伦兹力作用增加翼面壁面摩擦力,导致升力减小和阻力增加,流向洛伦兹力还导致翼型壁面压力下降,增加翼型升力和压差阻力;壁面摩擦力导致的升力降幅比壁面压力变化导致的升力增幅小,壁面压力变化起主导作用;洛伦兹力推力对阻力的降幅比压差阻力的增幅大,洛伦兹力推力起主导作用,因此阻力减小.     

Towards improving efficiency of control for blowing into a boundary layer through a permeable wall

The results of experimental and numerical investigations of the efficiency of control by an incompressible turbulent boundary layer with the help air blowing through a permeable wall fabricated with maintenance of most of the necessary requirements for the quality and configuration of microapertures and having a low effective roughness are analyzed. Various cases of modeling the process of air blowing into the boundary layer through a specified hi-tech finely perforated surface are considered, and the data for average parameters and characteristics of turbulence of the flow types under investigation are presented. A substantial decrease in the skin-friction coefficient along the model length, which can achieve 90% with increasing the blowing coefficient, is shown. The estimate of the energy consumption for the process of blowing under terrestrial conditions testifies to the high potential of this method of control capable to provide 4–5% gain in the total aerodynamic drag of a simple modeling configuration.     

Analysis of turbulent axisymmetric inner near wake

An analysis is presented describing the characteristics of mean velocity profile in the axisymmetric turbulent inner near-wake flow behind a body of revolution. The near wake is developing under zero streamwise pressure gradient and the upstream turbulent boundary layer is fully developed. It is shown that the boundary layer condition that exists at the trailing edge can be used to describe the mean velocity profiles in the inner near wake. It is shown that the logarithmic layer of the upstream turbulent boundary layer continues to be valid for some more distance in the near wake, and as the streamwise distance is increased, the logarithmic layer is slowly getting destroyed. It is also shown that the central line velocity exhibits a logarithmic behaviour for large streamwise distance. Results of the analysis have been validated using available experimental data.     

利用微气泡减小平板湍流摩阻实验研究

设计了一套实验装置研究微气泡减阻的效果.采用高速摄像机对二维平板微气泡湍流边界层进行了定量的可视化观察,用天平测量了平板的摩擦阻力,分析了不同通气量、来流速度、浮力对减阻性能的影响.结果表明,微气泡在高Reynolds数（Re=106）的流动中有效地减小了摩擦阻力,最大减阻率达到36%,证实了微气泡能显著降低平板摩擦阻力,实验结果也表明,随气体流量增加,减阻率增加.      

两类非对称涡流动所诱导的摇滚运动

文章详细讨论了两类非对称涡流动诱发的模型摇滚运动.第1类是针对旋成体机身组合体模型, 其摇滚运动是由前体非对称涡流动诱发的, 运功形态呈现不确定性, 由模型头尖部的扰动触发形成.文章提出了快速旋转头尖部扰动的控制技术, 以抑制该类模型的大攻角摇滚运动.第2类是针对非常规机身的组合体模型, 其摇滚运动的主控流动是非常规机身和机翼的前缘分离涡流动, 这些流动是由组合体模型的边界条件确定的, 从而运动形态具有很好的确定性.所以, 这类模型的自由摇滚运动必须通过改变边界条件来改变诱发摇滚运动的流动, 以达到抑制模型自由摇滚运动的目的.最后, 文章还讨论了这类运动是由非对称的机翼涡涡强主控的.      

Optimization of supersonic flows past thin bodies by using external effects on the flow

Problems of optimization of flows past a thin body of revolution and a slender profile at a small angle of attack in the presence of local energy release zones and an external force acting on the flow near the surface are considered. Analysis is based on an analytic theory of supersonic flow past thin bodies presented in previous papers. The following problems are considered: drag reduction of a thin body of revolution, lift force enhancement of a profile with infinite aspect ratio, attenuation of acoustic noise generated by supersonic flows past bodies.     

一维短沟槽复合准晶结构减阻效应及模拟分析

本文测试了人工构建的一维短沟槽复合准晶结构对流体的减阻性能,并与一维短沟槽复合周期结构和一维沟槽周期结构的流阻进行了对比.实验结果表明,一维短沟槽复合准晶结构的减阻效果优于一维短沟槽复合周期结构,其中一维短沟槽十二重复合准晶结构的减阻效果最佳,同时与一维沟槽周期结构具有同样的减阻效果.在机理分析方面,建立了二维光栅的夫琅禾费衍射波模型,对通过一维短沟槽复合准晶结构的波谱特征进行模拟分析. 频谱分析表明,经过二维准周期光栅的相干波强度谱具有谱带结构特征,抑制了大角度方向上的强峰形成.这一结果与流体流过一维短沟槽复合准晶结构相对应,展向上的准周期结构在激活边界层微扰动的同时,也使得二次涡分布比较均匀,从而抑制了展向强扰动的形成,所以能够有效减小流阻.