二维平板湍流边界层减阻研究

利用一套以位移传感器为主的弹性平衡装置,测量几种不同表面形状设计的平板在充分发展的二维湍流边界层中的减阻效果,并对其减阻机理进行研究。结果表明,大涡破碎器 LEBU(Large Eddy Break-up)和其它减阻装置的形状和布置对表面摩擦阻力有较大影响,在有些设计状态下的平板得到了净减阻。     

Development of an Intermittency Equation for the Modeling of the Supersonic/Hypersonic Boundary Layer Flow Transition

An intermittency transport equation is developed in this study to model the laminar-turbulence boundary layer transition at supersonic and hypersonic conditions. The model takes into account the effects of different instability modes associated with the variations in Mach numbers. The model equation is based on the intermittency factor γ concept and couples with the well-known SST k–ω eddy-viscosity model in the solution procedures. The particular features of the present model approach are that: (1) the fluctuating kinetic energy k includes the non-turbulent, as well as turbulent fluctuations; (2) the proposed transport equation for the intermittency factor γ triggers the transition onset through a source term; (3) through the introduction of a new length scale normal to wall, the present model employs the local variables only avoiding the use of the integral parameters, like the boundary layer thickness δ, which are often cost-ineffective with the modern CFD methods; (4) in the fully turbulent region, the model retreats to SST model. This model is validated with a number of available experiments on boundary layer transition including the incompressible, supersonic and hypersonic flows past flat plates, straight/flared cones at zero incidences, etc. It is demonstrated that the present model can be successfully applied to the engineering calculations of a variety of aerodynamic flow transition with a reasonably wide range of Mach numbers.     

Unsteady Boundary Layer on a Blunt Body in a Hypersonic Flow of Non-Uniform Dusty Gas

The unsteady heat transfer at the stagnation point on a blunt body traveling at hypersonic velocity through a layer of nonuniform dusty gas with low-inertia particles (not deposited on the body surface) is investigated. Using the matched asymptotic expansion method, the equations of the two-phase unsteady boundary layer near the symmetry axis of the body are derived with account for the polydispersity of the particles. The structure of the unsteady boundary layer and the variation of the friction and heat transfer coefficients at the stagnation point are studied numerically. Layered nonuniformities of the particle concentration and size are considered, the limits of variation of the thermal and mechanicals loads are found, and the effect of the dust polydispersity on the heat transfer is investigated.     

平板湍流边界层整体摩擦阻力的振荡性

本文分别用流场显示和阻力测量两种实验方法,证明了平板整体摩擦阻力存在着振荡性,并得到了其振荡的一些规律和特点。另外,提出了一个与时间相关联的内层速度分布模型。并对其合理性进行了研究,从而导出一个与时间相关联的整体摩擦阻力模型。     

基于当地流活塞理论的气动弹性计算方法研究

发展了一种高效、高精度的超音速、高超音速非定常气动力计算 方法------基于定常CFD技术的当地流活塞理论. 运用当地流活塞理论计算非定常 气动力，耦合结构运动方程，实现超音速、高超音速气动弹性的时域模拟. 运用这 种方法计算了一系列非定常气动力算例和颤振算例，并和原始活塞理论、非定 常Euler方程结果作了比较. 由于局部地使用活塞理论假设，这种方法大大地克服 了原始活塞理论对飞行马赫数、翼型厚度和飞行迎角的 限制. 与非定常Euler方程方法相比，当地流活塞理论的效率很高.     

Receptivity of Hypersonic Boundary Layer to Wall Disturbances

Theoretical analysis of hypersonic boundary-layer receptivity to wall disturbances is conducted using a combination of asymptotic and numerical methods. Excitation of the second mode by distributed and local forcing on a flat-plate surface is studied under adiabatic and cooled wall conditions. Analysis addresses receptivity to wall vibrations, periodic suction/blowing, and temperature disturbances. A strong excitation occurs in local regions where forcing is in resonance with normal waves. It is shown that the receptivity function tends to infinity as the resonance point tends to the branch point of the discrete spectrum that is typical for boundary layers on cool surfaces. Asymptotic analysis resolves this singularity and provides the receptivity coefficient in the branch-point vicinity. Numerical results indicate extremely high receptivity to vibrations and suction/blowing in the vicinity of the branch point located near the lower neutral branch of the Mack second mode. Received 5 September 2000 and accepted 7 September 2001     

Prehistory of Instability in a Hypersonic Boundary Layer

The initial phase of hypersonic boundary-layer transition comprising excitation of boundary-layer modes and their downstream evolution from receptivity regions to the unstable region (instability prehistory problem) is considered. The disturbance spectrum reveals the following features: (1) the first and second modes are synchronized with acoustic waves near the leading edge; (2) further downstream, the first mode is synchronized with entropy and vorticity waves; (3) near the lower neutral branch of the Mack second mode, the first mode is synchronized with the second mode. Disturbance behavior in Regions (2) and (3) is studied using the multiple-mode method accounting for interaction between modes due to mean-flow nonparallel effects. Analysis of the disturbance behavior in Region 3) provides the intermodal exchange rule coupling input and output amplitudes of the first and second modes. It is shown that Region (3) includes branch points at which disturbance group velocity and amplitude are singular. These singularities can cause difficulties in stability analyses. In Region (2), vorticity/entropy waves are partially swallowed by the boundary layer. They may effectively generate the Mack second mode near its lower neutral branch. Received 17 July 2000 and accepted 23 March 2001     

Study of a Mixing Layer Formed by a Supersonic Main Stream of Air and a Co-Flowing Supersonic Helium Jet

The development of large-scale organised motions in a compressible mixing layer is studied experimentally using holographic interferometry, pressure and turbulence measurements. The mixing layer was formed behind the base of a parallel strut with a Mach 2 air main stream and a co-flowing two-dimensional slot jet (aspect ratio = 45) of helium at a Mach number of 1.2. The mixing layer exhibited highly organised vortical structures which were elongated and inclined approximately 45–50° to the flow direction. The mixing layer showed a linear growth and the mean velocity data indicated self-similar behaviour at sufficiently downstream distances. The results have shown that the thickness of the primary boundary layer has a strong influence on the growth and structure of the mixing layer. This revised version was published online in July 2006 with corrections to the Cover Date.     

游泳衣料的表面摩阻测量

本文介绍用二维激光流速仪对游泳衣料的局部表面摩阻作对比性实验的一组测量结果.由于游泳衣表面为具有高度柔弹性的粗糙壁面,所以表面摩阻系数的值由离壁面稍远的对数律层的速度分布求得.实验结果表明,不同衣料的表面摩阻的差别可达90%左右,国产的单向弹性奥纶游泳衣的表面摩阻系数最小.由此可知,这种具有纵向纹理的衣料对于减少水对运动员的阻力最为有利.     

Effect of Free-Stream Turbulence on the Reduction of Surface Friction in a Turbulent Boundary Layer Behind LEBU-Devices

The effect of increased free-stream turbulence on the reduction of the surface friction coefficient c _f in a turbulent boundary layer behind large-eddy break-up (LEBU) devices is investigated using a gravimetric method. The turbulence level was ε ≈ 1.9–4.9 % and the turbulence scale L _e ≈ 40–110 mm. The boundary layer Reynolds number Re** was varied from 2300 to 7500, with the boundary layer thickness being varied on the range δ = 33–44 mm. It is shown that an increase in the turbulence level ε has almost no impact on the relative reduction of friction behind LEBU-devices, whereas, under similar conditions of elevated free-stream turbulence, for another method, namely, the use of surface riblets, the friction reduction may be more strongly expressed.     

Three-Wave Interactions of Disturbances in a Supersonic Boundary Layer

Within the framework of the weakly nonlinear stability theory, group interaction of disturbances in a supersonic boundary layer is considered. The disturbances are represented by two spatial packets of traveling instability waves (wave trains) with multiple frequencies. The possibility of energy redistribution in such wave systems in the case of three-wave resonant interactions of packet constituents is considered. The model is used to test the dynamics of unstable waves arising due to introduction of controlled high-intensity disturbances into a supersonic boundary layer. It is found that this mechanism is not the main one for the features of streamwise dynamics of such nonlinear waves being observed.     

皮肤往复摩擦条件下的损伤研究

选用成年健康活体兔皮肤替代残肢皮肤,在UMT-Ⅱ多功能摩擦磨损试验机上通过模拟残肢皮肤/接收腔界面间的黏着和中间过渡摩擦行为,对兔皮肤的摩擦系数、Ft-D曲线、能量损耗以及这两种摩擦行为所引起的兔皮肤摩擦损伤机理进行了研究.结果表明:在0.5或3.5 N法向力作用下,随着往复摩擦位移从±2.5 mm增加到±5 mm,兔皮肤的摩擦行为从黏着状态转变到中间过渡状态,往复摩擦过程中的能量损耗增加;由于中间过渡状态下的兔皮肤摩擦系数较高,能量损耗较大,因而造成的皮肤损伤程度比黏着状态严重;与人体手掌或脚掌皮肤相比,兔皮肤的角质层较薄,很难形成摩擦水泡.     

A Slender Chisel-Like Body in a Supersonic Stream

The wave drag of a chisel-tike slender ruled body in a supersonic stream is considered. The dependence of the drag on the body geometry is studied. A comparison with axisymmetric bodies and the von Karman ogive is drawn.     

Stability of the Hypersonic Shock Layer on a Flat Plate

The stability of hypersonic viscous gas flow in a shock layer in the neighborhood of a flat plate is considered. The stability of the velocity, temperature, density, and pressure profiles calculated on the basis of the complete viscous shock layer equations is investigated within the framework of the linear stability theory with allowance for the shock wave relations. The calculated perturbation growth rates and phase velocities are compared with the experimental data obtained by means of electron-beam fluorescence.     

Existence of Stationary Supersonic Flows Past a Pointed Body

In this paper we study the mathematical aspects of the stationary supersonic flow past a non-axisymmetric curved pointed body. The flow is described by a steady potential flow equation, which is a quasilinear hyperbolic equation of second order. We prove the local existence of the solution to this problem with a pointed shock attached at the tip of the pointed body, provided the pointed body is a perturbation of a circular cone, and the vertex angle of the approximate cone of the pointed body is less than a critical value. The solution is smooth in between the shock and the surface of the body. Consequently, such a structure of flow near the tip of the pointed body and its stability is verified mathematically. Accepted October 13, 2000?Published online January 22, 2001     

Reduction of the Induced Drag of a Supersonic Wing

The oblique wing effect, i.e., a reduction in the wave drag for given lift, cannot be realized for a delta wing with supersonic leading edges owing to the lift reduction in the wing mid-section. To preserve the effect, the disturbances generated by the delta wing vertex must be eliminated by adding a body (wedge) to the wing by replacing the streamsurfaces behind the shock with rigid surfaces. Moreover, using wing tip deflection, and thereby reducing the wave drag to zero, makes it possible to obtain a lift- drag ratio close to that of the limiting, infinitely long flat plate.     

堆焊熔敷层表面纳米晶层摩擦磨损性能研究

用预压力滚压技术在堆焊修复层表面制备纳米晶层.利用TEM、SEM分析技术研究表面纳米晶层微观结构,利用CETR-3型多功能摩擦磨损试验机考察在干摩擦条件下堆焊层表面纳米晶层的摩擦磨损性能.结果表明堆焊修复层表面经表面纳米化处理后,表面形成厚度约为10μm(晶粒尺寸小于100 nm)的纳米晶层,最表面层平均晶粒尺寸约为10 nm.纳米压痕试验表明纳米晶层的硬度提高,最表面纳米晶层的硬度约为原始堆焊层硬度的3倍.与原始堆焊试样相比,表面纳米化试样的摩擦系数降低了10%,磨损体积降低了25%~30%左右.表面纳米化样品的磨损机制由原始堆焊层的磨粒磨损和黏着磨损转变为磨粒磨损,分析表明晶粒细化导致的高硬度、低塑性是摩擦磨损性能改善和磨损机制改变的主要原因.     

Nonlinear Disturbances and Weak Discontinuities in a Supersonic Boundary Layer

The processes of wave disturbance propagation in a supersonic boundary layer with self-induced pressure [1–4] are analyzed. The application of a new mathematical apparatus, namely, the theory of characteristics for systems of differential equations with operator coefficients [5–8], makes it possible to obtain generalized characteristics of the discrete and continuous spectra of the governing system of equations. It is shown that the discontinuities in the derivatives of the solution of the boundary layer equations are concentrated on the generalized characteristics. It is established that in the process of flow evolution the amplitude of the weak discontinuity in the derivatives may increase without bound, which indicates the possibility of breaking of nonlinear waves traveling in the boundary layer.     

纯铜表面双层辉光离子渗钛合金层的摩擦磨损性能

采用双层辉光离子渗金属技术，在纯铜表面形成含钛的合金渗层；采用扫描电子显微镜观察分析磨损表面形貌，并分析了磨损机理．结果表明：纯铜表面经离子渗钛后形成了以金属问化合物Cu4Ti和含钛的α固溶体为主的合金渗层，从而使表面强度提高，磨损性能明显改善；纯铜磨损表面呈撕裂特征，而离子渗钛试样仅发生轻微擦伤．