Nonlinear instability research of longitudinal structure generated by roughness in unswept wing boundary layer

The results of experimental study of a nonlinear varicose instability of the streaky structure generated by roughness element in unswept-wing boundary layer are presented. Features of the varicose breakdown of longitudinal steady streaky structure such as modulation of structure in transverse and streamwise directions by secondary disturbance, occurrence of the new streaky structures and A-structures downstream are shown. Spatio-temporal pictures of the hot-wire visualization of flow during spatial evolution of the streaky structures under influence of secondary high-frequency disturbance are discussed. Features of the adverse pressure gradient influence upon processes of the nonlinear varicose instability evolution and flow structure are revealed. Essential influence of the adverse pressure gradient on evolution of disturbances in shown. Comparison of varicose instability of the streaky structures generated in two different ways (the roughness element as in the given work, and continuous air blowing as in the earlier published work) is the carried out. The work supported by the Ministry of Education and Science of the Russian Federation (Grant No. RNP. 2.1.2.3370) and by the Russian Foundation for Basic Research (Grant No. 05-01-00034).     

叶片弦向倾斜对损失发展的影响及叶片反弯降低损失机理的研究

早在六十年代初期,Ｓｍｉｔｈ提出了弦向倾斜叶片￣［１］。叶片的这种倾斜集叶片的后掠（叶片展向与气流不垂直）和上反（叶片表面与端壁斜交）于一身。根据理论分析可知,弦向倾斜叶片与周向倾斜叶片比较,在相同倾斜角下,它更能有效地抑制通道涡的形成和发展￣［２］。但是,到现在为止还没有实验数据证实这一计算结果。本文继文献￣［３］详细测量了弦向倾斜叶片叶栅由栅前至栅后诸截面上的气动参数。实验结果表明,弦向倾斜对损失的发展起到了与周向倾斜相类似的作用,但是前者比后者减小了叶栅进口段的流向逆压梯度,从而降低了二次旋涡损失。本文还测量了大转角常规直叶栅与反弯叶片叶栅端壁与叶片表面上的静压分布,探讨了反弯叶片降低损失的原因,认为：减小叶栅进口段流向逆压梯度,在叶片吸力面前部形成垂直于端壁的平行静压等值线、在中部形成反“Ｃ”型静压等值线,以及在流道内建立沿叶高的反“Ｃ”型静压分布,是反弯叶片降低损失的三要素。     

不同起爆方式对含铝炸药水中爆炸近场冲击波压力的影响

 采用SJZ-30和GSJ-15型高速扫描相机,对端面点起爆、侧边点起爆和中心点起爆方式下,HLZY-1含铝炸药水中爆炸近场冲击波传播过程进行了实验观测,通过数字化方法得到了炸药近场冲击波沿狭缝方向的扫描曲线和冲击波压力变化曲线。研究表明,起爆方式对炸药水中爆炸初始冲击波峰值压力以及近场冲击波峰值压力的衰减有重要的影响。研究结果可以为水中兵器战斗部的设计以及毁伤效能评估提供参考。     

Visualization of sinusoidal and varicose instabilities of streaks in a boundary layer

Nonlinear instabilities of boundary layer streaks are investigated experimentally. Extensive measurements visualizing the sinusoidal and varicose instabilities of streaky structures at nonlinear stage of the breakdown process in boundary layer are presented. The flow behaviour in the course of spatial evolution of the streaky structures with a secondary high-frequency disturbance generated on them is discussed. Various scenarios of origination and development of coherent vortex structures examined in physical experiments are considered. Specific features of the development of sinusoidal and varicose cases of destruction of the steady streamwise streaks are demonstrated, such as transverse and streamwise modulations of the streak by the secondary-disturbance frequency, appearance of new streaky structures in the downstream direction, and emergence and evolution of unsteady Λ-shaped structures localized in space in both cases.     

Stationary velocity and pressure gradients in a thermoacoustic stack.

The second-order time-averaged acoustics of a viscous, thermally conducting gas between closely spaced parallel plates is studied. The acoustic disturbance is studied by expanding the equations of fluid dynamics and heat transfer to second order in Mach number. The undisturbed state is allowed to have a nonzero temperature gradient. A set of coupled equations for the time-averaged pressure gradient, velocity, and temperature are obtained and solved. Particular attention is paid to the relation between the time-averaged mass flux and pressure gradient. An explicit expression is obtained relating the time-averaged pressure drop across a thermoacoustic stack to the time-averaged mass flux through the stack.     

Stability characteristic of hypersonic flow over a blunt wedge under freestream pulse wave

To investigate the stability characteristic of hypersonic flow under the action of a freestream pulse wave, a high-order finite difference method was employed to do direction numerical simulation (DNS) of hypersonic unsteady flow over an 8° half-wedge-angle blunt wedge with freestream slow acoustic wave. The evolution of disturbance wave modes in the boundary layer under a pulse wave and a continuous wave are compared, and the wall temperature effect on the hypersonic boundary layer stability for a pulse wave disturbance is discussed. Results show that, both for a pulse wave and a continuous wave in freestream, the disturbance waves inside the nose boundary layer are mainly a fundamental mode; the Fourier amplitude of pressure disturbance mode in the boundary layer for a pulse wave is far less than that for a continuous wave, and the band frequency of the former is wider than that of the latter. All disturbance modes decay rapidly along the streamwise in the nose boundary layer. In the non-nose boundary layer, the dominant mode is transferred from fundamental mode into second harmonic. The transformation of dominant mode for a pulse wave appears much earlier than that for a continuous wave. Different frequency disturbance modes present different changes along streamline in the boundary layer, and the frequency band narrows around the second harmonic mode along the streamwise. Keen competition and the transformation of energy exist among different modes in the boundary layer. Wall temperature modifies the stability characteristic of the hypersonic boundary layer, which presents little effect on the development of fundamental modes and cooling wall could accelerates the growth of the high frequency mode as well as the dominant mode transformation.     

Streak instability in near-wall turbulence revisited

The regeneration cycle of streaks and streamwise vortices plays a central role in the sustainment of near-wall turbulence. In particular, the streak breakdown phase in the regeneration cycle is the core process in the formation of the streamwise vortices, but its current understanding is limited particularly in a real turbulent environment. This study is aimed at gaining fundamental insight into the underlying physical mechanism of the streak breakdown in the presence of background turbulent fluctuation. We perform a numerical experiment based on direct numerical simulation, in which streaks are artificially generated by a body forcing computed from previous linear theory. Upon increasing the forcing amplitude, the artificially driven streaks are found to generate an intense fluctuation of the wall-normal and spanwise velocities in a fairly large range of amplitudes. This cross-streamwise velocity fluctuation shows its maximum at λ⁺_x ≈ 200 ? 300 (λ⁺_x is the inner-scaled streamwise wavelength), but it only appears for λ⁺_x ? 3000 ? 4000. Further examination with dynamic mode decomposition reveals that the related flow field is composed of sinuous meandering motion of the driven streaks and alternating cross-streamwise velocity structures, clearly reminiscent of sinuous-mode streak instability found in previous studies. Finally, it is shown that these structures are reasonably well aligned along the critical layer of the secondary instability, indicating that the surrounding turbulence does not significantly modify the inviscid inflectional mechanism of the streak breakdown via streak instability and/or streak transient growth.     

Tuning of turbulent boundary layer anisotropy for improved surface pressure and trailing-edge noise modeling

The modeling of the surface pressure spectrum beneath a turbulent boundary layer is investigated, focusing on the case of airfoil flows and associated trailing edge noise prediction using the so-called TNO model. This type of flow is characterized by the presence of an adverse pressure gradient along the airfoil chord. It is shown that discrepancies between measurements and results from the TNO model increase as the pressure gradient increases. The original model is modified by introducing anisotropy in the definition of the turbulent vertical velocity spectrum across the boundary layer and by considering a frequency-dependent vertical correlation length. The degree of anisotropy is directly related to the strength of the pressure gradient. It is shown that by appropriately normalizing the pressure gradient and by tuning the degree of anisotropy, experimental results can be closely reproduced by the modified model. The model is validated against Large Eddy Simulation results and additional wind tunnel measurements. It is further validated in the context of trailing edge noise for which the model formulation makes use of the above surface pressure spectrum.     

高重复频率触发模式皮秒扫描相机

讨论了高重复频率扫描电路的研制,利用此扫描电路研制了扫描相机,使用掺钛兰宝石激光器进行了时间分辨率的标定,使用半导体激光器作为光源进行了脉冲宽度的测试.最高工作频率为：1 MHz,时间分辨率为：1.8 ps.     

高超声速条件下7°直圆锥边界层转捩实验研究

在Ma=6低噪声风洞中开展了半锥角7?的直圆锥边界层转捩相关实验研究.利用响应频率达到MHz量级的高频压力传感器对圆锥壁面脉动压力进行了测量,研究了高超声速圆锥边界层中扰动波的发展过程.结果表明:高超声速圆锥边界层中第二模态扰动波产生的位置以及扰动波特征频率和波长等参数受雷诺数影响较大,当单位雷诺数从2×106m~(-1)增加到8×106m~(-1)时,第二模态波的特征频率从55 k Hz增加到226 k Hz;随着单位雷诺数增加,边界层中扰动增长速度加快,第二模态波出现在圆锥表面更靠近上游的位置;相同单位雷诺数条件下,随着第二模态波的向下游传播,其特征频率逐渐减小.通过对比发现自由来流湍流度对边界层中扰动波的发展同样有较大影响,自由来流湍流度降低,边界层中的第二模态波的特征频率明显减小.利用互相关分析得出第二模态扰动波在边界层中的传播速度大约为当地主流速度的0.8—0.9倍.在1?小攻角条件下,圆锥迎风面和背风面边界层发展呈现出明显的差异,背风面边界层中扰动发展提前,第二模态波出现在更靠近上游的位置,而迎风面中扰动发展受到抑制,第二模态波特征频率更大.     

小型条纹管数值模拟及实验研究

针对无人机载及星载激光成像雷达系统对条纹管的小型化、高空间分辨率与大探测面积的应用需求,研制了一台具有高边缘空间分辨能力、高亮度增益的小型条纹相机.采用球面光电阴极、球面荧光屏技术提高了条纹相机的边缘空间分辨率和探测面积,有利于增大激光成像雷达的探测视场;采用狭缝型加速电极代替传统栅网电极,有利于提高条纹相机的电耐性和可靠性;设计了加载高达-15 kV工作电压的像缩小型条纹管,增大了条纹管的亮度增益,有助于增大激光雷达系统的探测距离.测试结果显示：在有效工作面积16 mm×2 mm内,条纹管静态空间分辨率高于29.3 lp/mm@MTF=5%（MTF表示调制传递函数）,亮度增益高达39.4.条纹相机光电阴极处静态空间分辨率高于15 lp/mm@CTF=11.64%（CTF表示对比度传递函数）;边缘动态空间分辨率高于9.8 lp/mm@CTF=5.51%;时间分辨率优于54.6 ps@T_screen=4.3 ns（T_screen为全屏时间）且在整个工作面积内具有较高的一致性;动态范围为345：1@54.6 ps.同时,为满足不同的景深及探测精度需求,相机设置六个扫描档位,可以实现不同扫速下的超快速目标诊断.该条纹相机在无人机载及星载激光成像雷达探测中具有潜在的实用价值.     

Picosecond X-ray plasma radiation measurements

Direct picosecond measurements of X-ray laser plasma radiation were performed with a high-speed X-ray image-converter camera (ICC). This camera operates in the single-frame mode with an exposure time ranging from 5 ns to 0.5 μs and in the streak mode with 5 × 10⁹ to 5 × 10⁷ cm/s streak velocities. Its temporal resolution in the streak mode was calculated to be about 7 ps. A plasma was created by focussing 10 ps 1 to 2 joule laser pulses onto a titanium target placed in a vacuum chamber. The halfwidth of the recorded X-ray pulses varied from 30 to 60 ps.     

Generalized wall functions for turbulent flows with strong adverse pressure gradient

The generalized wall functions for turbulent flows with strong adverse pressure gradients are derived on the basis of the asymptotic theory of near-wall turbulence. The generalized wall functions have a correct asymptotic behavior in the limit of zero friction velocity and can be applied to computations of flows under a strong adverse pressure gradient and with separation or reattachment. Calculations of a turbulent boundary layer in a strong adverse pressure gradient with the aid of the developed modified k-ɛ model of turbulence and comparison with the experimental data validate the advantages of the generalized wall functions over traditional wall functions based on the logarithmic law of the wall.     

Simultaneous single-shot measurement of temperature and pressure along a one-dimensional line by use of laser-induced thermal grating spectroscopy

We report a new technique, based on laser-induced thermal grating spectroscopy (LITGS), for time- and space-resolved simultaneous measurement of temperature and pressure along a one-dimensional line. LITGS signals generated in NO2/N2 mixtures along a 5 mm line produce a time-varying image that is recorded on a streak camera. The temperature is derived with a precision of 0.3% from the streak images using a rapid Fourier method with a spatial resolution of 150 microm along the line. The principle of pressure measurement is demonstrated using a sequence of images, and a simple extension of the method to single-shot pressure measurement is discussed.     

同步相机测量任意频率光信号时的S/N理论分析

本文从理论上分析了同步扫描相机在测量由双波长激光器产生的差频信号时信噪比的问题.这一差频信号的频率和同步相机的扫描频率并非整数倍关系.我们从光电阴极的发射噪音(shotnoise)理论出发,得出了在这种特殊应用情况下相机的信嗓比比正常应用情况下(即入射光脉冲的频率和扫描频率为整数倍关系)至少要小23倍.     

Three-dimensional analysis of blade force and sound generation for an annular cascade in distorted flows

An unsteady lifting-surface theory for a rotating subsonic annular cascade has been developed to predict the unsteady blade forces and the acoustic power generation caused by interaction of blades with inlet distortions or wakes. Disturbance pressure and velocity fields induced by the rotor blades with fluctuating blade force are expressed in terms of the blade force distribution and kernel functions. The spanwise distribution of the blade force is given as a sum of blade force modes, and the kernel functions are resolved into the corresponding modal components. The sound pressure and intensity are expressed as a sum of acoustic modes, the modal components of which are given in terms of the blade force mode components.Numerical computations have been conducted .for interaction with the external disturbance flows that are sinusoidal in the circumferential direction, but possess a phase skewing in the radial direction. Correlations among the acoustic modes, the blade force modes and the flow patterns of the external disturbance have been investigated. When the predominant acoustic mode is subresonant, the blade force amplitude is reduced by the three-dimensional effect, which is lessened as the frequency increases. At deeply superresonant states, however, the three-dimensional effect upon the spanwise average of the blade force amplitude is small. The generated sound power is effectively reduced by increasing the radial non-uniformity of the external disturbance.     

Further improvement and analysis of CCD scheme: Dissipation discretization and de-aliasing properties

In this paper, we further analyze a combined compact difference (CCD) scheme proposed recently [T.K. Sengupta, V. Lakshmanan, V.V.S.N. Vijay, A new combined stable and dispersion relation preserving compact scheme for non-periodic problems, J. Comput. Phys. 228 (8) (2009) 3048–3071] for its dissipation discretization properties to show that its superiority also helps in controlling aliasing error for a benchmark internal flow. However, application of the same CCD method to study the receptivity of a boundary layer experiencing adverse pressure gradient is not successful. This is traced to the nature of the equilibrium flow where the better dissipation property is not helpful in the inviscid part of the flow, where the aliasing problems continue to persist. A further modification is proposed to the CCD method here to solve complex physical problems requiring information on higher order disturbance quantities – as in problems of flow receptivity and instability.     

Stability of hydromagnetic Dean flow between two arbitrarily spaced concentric circular cylinders in the presence of a uniform axial magnetic field

The effect of a uniform axial magnetic field on the stability of the flow of an incompressible viscous electrically conducting fluid between two arbitrarily spaced concentric circular cylinders driven by a constant azimuthal pressure gradient is studied. The linearized stability equations for steady axisymmetric disturbances form an eigenvalue problem, which are solved by using a classical Runge–Kutta scheme combined with a shooting method, termed unit disturbance method. It is observed that for fixed gap width, the magnetic field has a stabilizing influence on the flow for both perfectly conducting and nonconducting walls. It is also found that for a given value of magnetic parameter, stabilization is more as the gap width increases. Further the electrically nonconducting walls are found to be more destabilizing than the perfectly conducting walls. The critical value of the radii ratio (0<η<1) beyond which the first unstable mode becomes nonaxisymmetric is determined for various values of the magnetic parameter.     

一种用于荧光皮秒时间分辨光谱的测试系统

本文详细描述了一种由氩离子锁模激光器、样品池、分光系统及微微秒条纹相机构成的用于测试低强度荧光微微秒时间分辨光谱的系统。给出了典型样品的测试结果:时间分辨率为10ps,光谱范围为500Å—800Å。最后对测量结果进行了分析讨论。     

Reversed rotation of limit cycle oscillation and dynamics of low-intermediate-high confinement transition

The dynamics of the confinement transition from L mode to H mode(LH) is investigated in detail theoretically via the extended three-wave coupling model describing the interaction of turbulence and zonal flow(ZF) for the first time.Thereinto, turbulence is divided into a positive-frequency(PF) wave and a negative-frequency(NF) one, and the gradient of pressure is added as the auxiliary energy for the system. The LH confinement transition is observed for a sufficiently high input energy. Moreover, it is found that the rotation direction of the limit cycle oscillation(LCO) of PF wave and pressure gradient is reversed during the transition. The mechanism is illustrated by exploring the wave phases. The results presented here provide a new insight into the analysis of the LH transition, which is helpful for the experiments on the fusion devices.